From 4a7182852450acc9050e80861316ff83a2b1d01e Mon Sep 17 00:00:00 2001 From: Derek Slaughter Date: Mon, 13 May 2024 11:54:06 -0400 Subject: [PATCH] Add a 5MW monopile example which uses SubDyn --- examples/NREL_5MW_Monopile/.gitignore | 1 + .../NREL_5MW_Monopile/Airfoils/Cylinder1.dat | 59 + .../Airfoils/Cylinder1_coords.txt | 407 + .../NREL_5MW_Monopile/Airfoils/Cylinder2.dat | 60 + .../Airfoils/Cylinder2_coords.txt | 407 + .../NREL_5MW_Monopile/Airfoils/DU21_A17.dat | 196 + .../Airfoils/DU21_A17_coords.txt | 407 + .../NREL_5MW_Monopile/Airfoils/DU25_A17.dat | 194 + .../Airfoils/DU25_A17_coords.txt | 407 + .../NREL_5MW_Monopile/Airfoils/DU30_A17.dat | 198 + .../Airfoils/DU30_A17_coords.txt | 407 + .../NREL_5MW_Monopile/Airfoils/DU35_A17.dat | 189 + .../Airfoils/DU35_A17_coords.txt | 407 + .../NREL_5MW_Monopile/Airfoils/DU40_A17.dat | 190 + .../Airfoils/DU40_A17_coords.txt | 407 + .../NREL_5MW_Monopile/Airfoils/NACA64_A17.dat | 181 + .../Airfoils/NACA64_A17_coords.txt | 407 + .../NREL_5MW_AeroDyn_blade.dat | 28 + .../NREL_5MW_ElastoDyn_Blade.dat | 83 + .../NREL_5MW_Monopile/NREL_5MW_InflowWind.dat | 71 + .../NREL_5MW_Monopile/NREL_5MW_Monopile.fst | 71 + .../NREL_5MW_Monopile/NREL_5MW_Monopile.json | 6556 +++++++++++++++++ .../NREL_5MW_Monopile_AeroDyn15.dat | 95 + .../NREL_5MW_Monopile_ElastoDyn.dat | 135 + .../NREL_5MW_Monopile_ElastoDyn_Tower.dat | 54 + .../NREL_5MW_Monopile_HydroDyn.dat | 151 + .../NREL_5MW_Monopile_ServoDyn.dat | 110 + .../NREL_5MW_Monopile_SubDyn.dat | 99 + 28 files changed, 11977 insertions(+) create mode 100644 examples/NREL_5MW_Monopile/.gitignore create mode 100644 examples/NREL_5MW_Monopile/Airfoils/Cylinder1.dat create mode 100644 examples/NREL_5MW_Monopile/Airfoils/Cylinder1_coords.txt create mode 100644 examples/NREL_5MW_Monopile/Airfoils/Cylinder2.dat create mode 100644 examples/NREL_5MW_Monopile/Airfoils/Cylinder2_coords.txt create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU21_A17.dat create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU21_A17_coords.txt create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU25_A17.dat create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU25_A17_coords.txt create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU30_A17.dat create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU30_A17_coords.txt create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU35_A17.dat create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU35_A17_coords.txt create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU40_A17.dat create mode 100644 examples/NREL_5MW_Monopile/Airfoils/DU40_A17_coords.txt create mode 100644 examples/NREL_5MW_Monopile/Airfoils/NACA64_A17.dat create mode 100644 examples/NREL_5MW_Monopile/Airfoils/NACA64_A17_coords.txt create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_AeroDyn_blade.dat create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_ElastoDyn_Blade.dat create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_InflowWind.dat create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_Monopile.fst create mode 100755 examples/NREL_5MW_Monopile/NREL_5MW_Monopile.json create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_Monopile_AeroDyn15.dat create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ElastoDyn.dat create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ElastoDyn_Tower.dat create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_Monopile_HydroDyn.dat create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ServoDyn.dat create mode 100644 examples/NREL_5MW_Monopile/NREL_5MW_Monopile_SubDyn.dat diff --git a/examples/NREL_5MW_Monopile/.gitignore b/examples/NREL_5MW_Monopile/.gitignore new file mode 100644 index 0000000..2ed7b8e --- /dev/null +++ b/examples/NREL_5MW_Monopile/.gitignore @@ -0,0 +1 @@ +NREL_5MW_Monopile/ \ No newline at end of file diff --git a/examples/NREL_5MW_Monopile/Airfoils/Cylinder1.dat b/examples/NREL_5MW_Monopile/Airfoils/Cylinder1.dat new file mode 100644 index 0000000..d9e59b2 --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/Cylinder1.dat @@ -0,0 +1,59 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! Round root section with a Cd of 0.50 +! Made by Jason Jonkman +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"Cylinder1_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + 0 alpha0 ! 0-lift angle of attack, depends on airfoil. + 0 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + 0 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + 0 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.5 Cd0 ! 2D drag coefficient value at 0-lift. + 0 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.5000 0.0 + 0.00 0.000 0.5000 0.0 + 180.00 0.000 0.5000 0.0 +! ------------------------------------------------------------------------------ + diff --git a/examples/NREL_5MW_Monopile/Airfoils/Cylinder1_coords.txt b/examples/NREL_5MW_Monopile/Airfoils/Cylinder1_coords.txt new file mode 100644 index 0000000..30663b7 --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/Cylinder1_coords.txt @@ -0,0 +1,407 @@ + 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c +0.5 0 +! coordinates of airfoil shape +! cylinder (interpolated to 399 points) +! x/c y/c +1.000000 0.000000 +0.996600 0.058210 +0.993140 0.082541 +0.989610 0.101400 +0.986010 0.117449 +0.982350 0.131676 +0.978630 0.144614 +0.974840 0.156611 +0.970980 0.167863 +0.967060 0.178480 +0.963070 0.188590 +0.959020 0.198244 +0.954900 0.207523 +0.950720 0.216452 +0.946470 0.225088 +0.942160 0.233441 +0.937780 0.241555 +0.933330 0.249450 +0.928820 0.257125 +0.924250 0.264598 +0.919610 0.271896 +0.914900 0.279030 +0.910130 0.285995 +0.905290 0.292814 +0.900390 0.299479 +0.895420 0.306011 +0.890390 0.312403 +0.885290 0.318672 +0.880130 0.324809 +0.874900 0.330832 +0.869610 0.336732 +0.864250 0.342523 +0.858820 0.348207 +0.853330 0.353777 +0.847780 0.359234 +0.842160 0.364591 +0.836470 0.369849 +0.830720 0.374999 +0.824900 0.380053 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-0.082541 +0.996600 -0.058210 +1.000000 0.000000 diff --git a/examples/NREL_5MW_Monopile/Airfoils/Cylinder2.dat b/examples/NREL_5MW_Monopile/Airfoils/Cylinder2.dat new file mode 100644 index 0000000..f6e6a9f --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/Cylinder2.dat @@ -0,0 +1,60 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! Round root section with a Cd of 0.35 +! Made by Jason Jonkman +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"Cylinder2_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + 0 alpha0 ! 0-lift angle of attack, depends on airfoil. + 0 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + 0 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + 0 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.35 Cd0 ! 2D drag coefficient value at 0-lift. + 0 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.3500 0.0 + 0.00 0.000 0.3500 0.0 + 180.00 0.000 0.3500 0.0 +! ------------------------------------------------------------------------------ + diff --git a/examples/NREL_5MW_Monopile/Airfoils/Cylinder2_coords.txt b/examples/NREL_5MW_Monopile/Airfoils/Cylinder2_coords.txt new file mode 100644 index 0000000..ba5741b --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/Cylinder2_coords.txt @@ -0,0 +1,407 @@ + 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c +0.41667 0 +! coordinates of airfoil shape +! cylinder (interpolated to 399 points) +! x/c y/c +1.000000 0.000000 +0.996600 0.058210 +0.993140 0.082541 +0.989610 0.101400 +0.986010 0.117449 +0.982350 0.131676 +0.978630 0.144614 +0.974840 0.156611 +0.970980 0.167863 +0.967060 0.178480 +0.963070 0.188590 +0.959020 0.198244 +0.954900 0.207523 +0.950720 0.216452 +0.946470 0.225088 +0.942160 0.233441 +0.937780 0.241555 +0.933330 0.249450 +0.928820 0.257125 +0.924250 0.264598 +0.919610 0.271896 +0.914900 0.279030 +0.910130 0.285995 +0.905290 0.292814 +0.900390 0.299479 +0.895420 0.306011 +0.890390 0.312403 +0.885290 0.318672 +0.880130 0.324809 +0.874900 0.330832 +0.869610 0.336732 +0.864250 0.342523 +0.858820 0.348207 +0.853330 0.353777 +0.847780 0.359234 +0.842160 0.364591 +0.836470 0.369849 +0.830720 0.374999 +0.824900 0.380053 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-0.082541 +0.996600 -0.058210 +1.000000 0.000000 diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU21_A17.dat b/examples/NREL_5MW_Monopile/Airfoils/DU21_A17.dat new file mode 100644 index 0000000..9fb97f0 --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU21_A17.dat @@ -0,0 +1,196 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU21 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU21_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -4.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 8 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -8 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.4144 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.5324 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.006 Cd0 ! 2D drag coefficient value at 0-lift. + -0.121 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 142 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0185 0.0000 + -175.00 0.394 0.0332 0.1978 + -170.00 0.788 0.0945 0.3963 + -160.00 0.670 0.2809 0.2738 + -155.00 0.749 0.3932 0.3118 + -150.00 0.797 0.5112 0.3413 + -145.00 0.818 0.6309 0.3636 + -140.00 0.813 0.7485 0.3799 + -135.00 0.786 0.8612 0.3911 + -130.00 0.739 0.9665 0.3980 + -125.00 0.675 1.0625 0.4012 + -120.00 0.596 1.1476 0.4014 + -115.00 0.505 1.2206 0.3990 + -110.00 0.403 1.2805 0.3943 + -105.00 0.294 1.3265 0.3878 + -100.00 0.179 1.3582 0.3796 + -95.00 0.060 1.3752 0.3700 + -90.00 -0.060 1.3774 0.3591 + -85.00 -0.179 1.3648 0.3471 + -80.00 -0.295 1.3376 0.3340 + -75.00 -0.407 1.2962 0.3199 + -70.00 -0.512 1.2409 0.3049 + -65.00 -0.608 1.1725 0.2890 + -60.00 -0.693 1.0919 0.2722 + -55.00 -0.764 1.0002 0.2545 + -50.00 -0.820 0.8990 0.2359 + -45.00 -0.857 0.7900 0.2163 + -40.00 -0.875 0.6754 0.1958 + -35.00 -0.869 0.5579 0.1744 + -30.00 -0.838 0.4405 0.1520 + -25.00 -0.791 0.3256 0.1262 + -24.00 -0.794 0.3013 0.1170 + -23.00 -0.805 0.2762 0.1059 + -22.00 -0.821 0.2506 0.0931 + -21.00 -0.843 0.2246 0.0788 + -20.00 -0.869 0.1983 0.0631 + -19.00 -0.899 0.1720 0.0464 + -18.00 -0.931 0.1457 0.0286 + -17.00 -0.964 0.1197 0.0102 + -16.00 -0.999 0.0940 -0.0088 + -15.00 -1.033 0.0689 -0.0281 + -14.50 -1.050 0.0567 -0.0378 + -12.01 -0.953 0.0271 -0.0349 + -11.00 -0.900 0.0303 -0.0361 + -9.98 -0.827 0.0287 -0.0464 + -8.12 -0.536 0.0124 -0.0821 + -7.62 -0.467 0.0109 -0.0924 + -7.11 -0.393 0.0092 -0.1015 + -6.60 -0.323 0.0083 -0.1073 + -6.50 -0.311 0.0089 -0.1083 + -6.00 -0.245 0.0082 -0.1112 + -5.50 -0.178 0.0074 -0.1146 + -5.00 -0.113 0.0069 -0.1172 + -4.50 -0.048 0.0065 -0.1194 + -4.00 0.016 0.0063 -0.1213 + -3.50 0.080 0.0061 -0.1232 + -3.00 0.145 0.0058 -0.1252 + -2.50 0.208 0.0057 -0.1268 + -2.00 0.270 0.0057 -0.1282 + -1.50 0.333 0.0057 -0.1297 + -1.00 0.396 0.0057 -0.1310 + -0.50 0.458 0.0057 -0.1324 + 0.00 0.521 0.0057 -0.1337 + 0.50 0.583 0.0057 -0.1350 + 1.00 0.645 0.0058 -0.1363 + 1.50 0.706 0.0058 -0.1374 + 2.00 0.768 0.0059 -0.1385 + 2.50 0.828 0.0061 -0.1395 + 3.00 0.888 0.0063 -0.1403 + 3.50 0.948 0.0066 -0.1406 + 4.00 0.996 0.0071 -0.1398 + 4.50 1.046 0.0079 -0.1390 + 5.00 1.095 0.0090 -0.1378 + 5.50 1.145 0.0103 -0.1369 + 6.00 1.192 0.0113 -0.1353 + 6.50 1.239 0.0122 -0.1338 + 7.00 1.283 0.0131 -0.1317 + 7.50 1.324 0.0139 -0.1291 + 8.00 1.358 0.0147 -0.1249 + 8.50 1.385 0.0158 -0.1213 + 9.00 1.403 0.0181 -0.1177 + 9.50 1.401 0.0211 -0.1142 + 10.00 1.358 0.0255 -0.1103 + 10.50 1.313 0.0301 -0.1066 + 11.00 1.287 0.0347 -0.1032 + 11.50 1.274 0.0401 -0.1002 + 12.00 1.272 0.0468 -0.0971 + 12.50 1.273 0.0545 -0.0940 + 13.00 1.273 0.0633 -0.0909 + 13.50 1.273 0.0722 -0.0883 + 14.00 1.272 0.0806 -0.0865 + 14.50 1.273 0.0900 -0.0854 + 15.00 1.275 0.0987 -0.0849 + 15.50 1.281 0.1075 -0.0847 + 16.00 1.284 0.1170 -0.0850 + 16.50 1.296 0.1270 -0.0858 + 17.00 1.306 0.1368 -0.0869 + 17.50 1.308 0.1464 -0.0883 + 18.00 1.308 0.1562 -0.0901 + 18.50 1.308 0.1664 -0.0922 + 19.00 1.308 0.1770 -0.0949 + 19.50 1.307 0.1878 -0.0980 + 20.00 1.311 0.1987 -0.1017 + 20.50 1.325 0.2100 -0.1059 + 21.00 1.324 0.2214 -0.1105 + 22.00 1.277 0.2499 -0.1172 + 23.00 1.229 0.2786 -0.1239 + 24.00 1.182 0.3077 -0.1305 + 25.00 1.136 0.3371 -0.1370 + 26.00 1.093 0.3664 -0.1433 + 28.00 1.017 0.4246 -0.1556 + 30.00 0.962 0.4813 -0.1671 + 32.00 0.937 0.5356 -0.1778 + 35.00 0.947 0.6127 -0.1923 + 40.00 0.950 0.7396 -0.2154 + 45.00 0.928 0.8623 -0.2374 + 50.00 0.884 0.9781 -0.2583 + 55.00 0.821 1.0846 -0.2782 + 60.00 0.740 1.1796 -0.2971 + 65.00 0.646 1.2617 -0.3149 + 70.00 0.540 1.3297 -0.3318 + 75.00 0.425 1.3827 -0.3476 + 80.00 0.304 1.4202 -0.3625 + 85.00 0.179 1.4423 -0.3763 + 90.00 0.053 1.4512 -0.3890 + 95.00 -0.073 1.4480 -0.4004 + 100.00 -0.198 1.4294 -0.4105 + 105.00 -0.319 1.3954 -0.4191 + 110.00 -0.434 1.3464 -0.4260 + 115.00 -0.541 1.2829 -0.4308 + 120.00 -0.637 1.2057 -0.4333 + 125.00 -0.720 1.1157 -0.4330 + 130.00 -0.787 1.0144 -0.4294 + 135.00 -0.836 0.9033 -0.4219 + 140.00 -0.864 0.7845 -0.4098 + 145.00 -0.869 0.6605 -0.3922 + 150.00 -0.847 0.5346 -0.3682 + 155.00 -0.795 0.4103 -0.3364 + 160.00 -0.711 0.2922 -0.2954 + 170.00 -0.788 0.0969 -0.3966 + 175.00 -0.394 0.0334 -0.1978 + 180.00 0.000 0.0185 0.0000 diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU21_A17_coords.txt b/examples/NREL_5MW_Monopile/Airfoils/DU21_A17_coords.txt new file mode 100644 index 0000000..72e36bf --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU21_A17_coords.txt @@ -0,0 +1,407 @@ + 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! DU 93-W-210.lm +! x/c y/c +1.00000 0.00194 +0.99660 0.00304 +0.99314 0.00411 +0.98961 0.00516 +0.98601 0.00618 +0.98235 0.00720 +0.97863 0.00823 +0.97484 0.00927 +0.97098 0.01033 +0.96706 0.01139 +0.96307 0.01246 +0.95902 0.01354 +0.95490 0.01463 +0.95072 0.01573 +0.94647 0.01684 +0.94216 0.01797 +0.93778 0.01911 +0.93333 0.02026 +0.92882 0.02142 +0.92425 0.02260 +0.91961 0.02379 +0.91490 0.02499 +0.91013 0.02621 +0.90529 0.02744 +0.90039 0.02869 +0.89542 0.02995 +0.89039 0.03122 +0.88529 0.03250 +0.88013 0.03379 +0.87490 0.03510 +0.86961 0.03643 +0.86425 0.03776 +0.85882 0.03912 +0.85333 0.04048 +0.84778 0.04186 +0.84216 0.04326 +0.83647 0.04466 +0.83072 0.04608 +0.82490 0.04752 +0.81902 0.04896 +0.81307 0.05041 +0.80706 0.05188 +0.80098 0.05336 +0.79484 0.05484 +0.78863 0.05634 +0.78235 0.05784 +0.77601 0.05936 +0.76961 0.06088 +0.76314 0.06242 +0.75660 0.06396 +0.75000 0.06550 +0.74333 0.06706 +0.73667 0.06860 +0.73000 0.07014 +0.72333 0.07167 +0.71667 0.07320 +0.71000 0.07472 +0.70333 0.07624 +0.69667 0.07774 +0.69000 0.07924 +0.68333 0.08072 +0.67667 0.08220 +0.67000 0.08366 +0.66333 0.08511 +0.65667 0.08655 +0.65000 0.08798 +0.64333 0.08940 +0.63667 0.09080 +0.63000 0.09220 +0.62333 0.09357 +0.61667 0.09492 +0.61000 0.09626 +0.60333 0.09759 +0.59667 0.09889 +0.59000 0.10017 +0.58333 0.10143 +0.57667 0.10267 +0.57000 0.10389 +0.56333 0.10509 +0.55667 0.10627 +0.55000 0.10742 +0.54333 0.10854 +0.53667 0.10964 +0.53000 0.11071 +0.52333 0.11175 +0.51667 0.11277 +0.51000 0.11375 +0.50333 0.11470 +0.49667 0.11562 +0.49000 0.11650 +0.48333 0.11734 +0.47667 0.11813 +0.47000 0.11889 +0.46333 0.11960 +0.45667 0.12027 +0.45000 0.12089 +0.44333 0.12147 +0.43667 0.12200 +0.43000 0.12249 +0.42333 0.12292 +0.41667 0.12331 +0.41000 0.12365 +0.40333 0.12394 +0.39667 0.12418 +0.39000 0.12436 +0.38333 0.12449 +0.37667 0.12457 +0.37000 0.12459 +0.36333 0.12455 +0.35667 0.12446 +0.35000 0.12431 +0.34333 0.12411 +0.33667 0.12385 +0.33000 0.12353 +0.32333 0.12317 +0.31667 0.12275 +0.31000 0.12228 +0.30333 0.12175 +0.29667 0.12117 +0.29000 0.12053 +0.28333 0.11984 +0.27667 0.11910 +0.27000 0.11829 +0.26333 0.11744 +0.25667 0.11653 +0.25000 0.11557 +0.24342 0.11456 +0.23693 0.11351 +0.23053 0.11243 +0.22421 0.11130 +0.21798 0.11015 +0.21184 0.10896 +0.20579 0.10773 +0.19982 0.10648 +0.19395 0.10520 +0.18816 0.10389 +0.18245 0.10255 +0.17684 0.10119 +0.17131 0.09980 +0.16587 0.09839 +0.16052 0.09696 +0.15526 0.09550 +0.15008 0.09403 +0.14499 0.09254 +0.13999 0.09103 +0.13508 0.08950 +0.13026 0.08796 +0.12552 0.08641 +0.12087 0.08483 +0.11631 0.08325 +0.11183 0.08165 +0.10745 0.08004 +0.10315 0.07843 +0.09893 0.07679 +0.09481 0.07516 +0.09077 0.07351 +0.08683 0.07186 +0.08297 0.07021 +0.07919 0.06854 +0.07551 0.06687 +0.07191 0.06520 +0.06840 0.06353 +0.06498 0.06185 +0.06164 0.06017 +0.05840 0.05850 +0.05524 0.05682 +0.05217 0.05515 +0.04918 0.05348 +0.04629 0.05181 +0.04348 0.05015 +0.04076 0.04849 +0.03812 0.04683 +0.03558 0.04519 +0.03312 0.04356 +0.03075 0.04194 +0.02847 0.04033 +0.02627 0.03874 +0.02417 0.03716 +0.02215 0.03560 +0.02022 0.03404 +0.01837 0.03249 +0.01662 0.03094 +0.01495 0.02940 +0.01337 0.02785 +0.01187 0.02630 +0.01047 0.02476 +0.00915 0.02322 +0.00792 0.02169 +0.00678 0.02017 +0.00572 0.01864 +0.00476 0.01713 +0.00388 0.01562 +0.00309 0.01410 +0.00238 0.01253 +0.00177 0.01094 +0.00124 0.00923 +0.00080 0.00740 +0.00044 0.00537 +0.00018 0.00333 +0.00000 0.00000 +0.00018 -0.00292 +0.00044 -0.00443 +0.00080 -0.00589 +0.00124 -0.00727 +0.00177 -0.00864 +0.00238 -0.00998 +0.00309 -0.01134 +0.00388 -0.01266 +0.00476 -0.01397 +0.00572 -0.01526 +0.00678 -0.01656 +0.00792 -0.01785 +0.00915 -0.01914 +0.01047 -0.02044 +0.01187 -0.02174 +0.01337 -0.02306 +0.01495 -0.02438 +0.01662 -0.02571 +0.01837 -0.02705 +0.02022 -0.02841 +0.02215 -0.02976 +0.02417 -0.03112 +0.02627 -0.03248 +0.02847 -0.03384 +0.03075 -0.03520 +0.03312 -0.03655 +0.03558 -0.03789 +0.03812 -0.03923 +0.04076 -0.04056 +0.04348 -0.04188 +0.04629 -0.04319 +0.04918 -0.04449 +0.05217 -0.04579 +0.05524 -0.04708 +0.05840 -0.04836 +0.06164 -0.04963 +0.06498 -0.05089 +0.06840 -0.05215 +0.07191 -0.05340 +0.07551 -0.05464 +0.07919 -0.05587 +0.08297 -0.05709 +0.08683 -0.05831 +0.09077 -0.05951 +0.09481 -0.06071 +0.09893 -0.06189 +0.10315 -0.06306 +0.10745 -0.06422 +0.11183 -0.06536 +0.11631 -0.06648 +0.12087 -0.06759 +0.12552 -0.06868 +0.13026 -0.06975 +0.13508 -0.07079 +0.13999 -0.07182 +0.14499 -0.07282 +0.15008 -0.07380 +0.15526 -0.07476 +0.16052 -0.07568 +0.16587 -0.07658 +0.17131 -0.07746 +0.17684 -0.07830 +0.18245 -0.07911 +0.18816 -0.07989 +0.19395 -0.08063 +0.19982 -0.08134 +0.20579 -0.08201 +0.21184 -0.08264 +0.21798 -0.08324 +0.22421 -0.08380 +0.23053 -0.08432 +0.23693 -0.08479 +0.24342 -0.08523 +0.25000 -0.08561 +0.25667 -0.08595 +0.26333 -0.08624 +0.27000 -0.08648 +0.27667 -0.08667 +0.28333 -0.08680 +0.29000 -0.08689 +0.29667 -0.08693 +0.30333 -0.08692 +0.31000 -0.08686 +0.31667 -0.08676 +0.32333 -0.08660 +0.33000 -0.08640 +0.33667 -0.08615 +0.34333 -0.08586 +0.35000 -0.08553 +0.35667 -0.08515 +0.36333 -0.08473 +0.37000 -0.08427 +0.37667 -0.08376 +0.38333 -0.08322 +0.39000 -0.08263 +0.39667 -0.08200 +0.40333 -0.08134 +0.41000 -0.08062 +0.41667 -0.07987 +0.42333 -0.07908 +0.43000 -0.07824 +0.43667 -0.07736 +0.44333 -0.07644 +0.45000 -0.07548 +0.45667 -0.07448 +0.46333 -0.07343 +0.47000 -0.07235 +0.47667 -0.07122 +0.48333 -0.07006 +0.49000 -0.06886 +0.49667 -0.06763 +0.50333 -0.06636 +0.51000 -0.06506 +0.51667 -0.06373 +0.52333 -0.06237 +0.53000 -0.06097 +0.53667 -0.05955 +0.54333 -0.05810 +0.55000 -0.05663 +0.55667 -0.05513 +0.56333 -0.05361 +0.57000 -0.05207 +0.57667 -0.05050 +0.58333 -0.04892 +0.59000 -0.04732 +0.59667 -0.04571 +0.60333 -0.04408 +0.61000 -0.04243 +0.61667 -0.04078 +0.62333 -0.03911 +0.63000 -0.03744 +0.63667 -0.03576 +0.64333 -0.03409 +0.65000 -0.03241 +0.65667 -0.03073 +0.66333 -0.02906 +0.67000 -0.02740 +0.67667 -0.02574 +0.68333 -0.02411 +0.69000 -0.02248 +0.69667 -0.02088 +0.70333 -0.01930 +0.71000 -0.01774 +0.71667 -0.01620 +0.72333 -0.01470 +0.73000 -0.01323 +0.73667 -0.01179 +0.74333 -0.01039 +0.75000 -0.00903 +0.75660 -0.00772 +0.76314 -0.00647 +0.76961 -0.00528 +0.77601 -0.00416 +0.78235 -0.00308 +0.78863 -0.00207 +0.79484 -0.00112 +0.80098 -0.00023 +0.80706 0.00060 +0.81307 0.00136 +0.81902 0.00207 +0.82490 0.00273 +0.83072 0.00333 +0.83647 0.00387 +0.84216 0.00435 +0.84778 0.00479 +0.85333 0.00517 +0.85882 0.00550 +0.86425 0.00578 +0.86961 0.00601 +0.87490 0.00620 +0.88013 0.00633 +0.88529 0.00643 +0.89039 0.00648 +0.89542 0.00649 +0.90039 0.00646 +0.90529 0.00639 +0.91013 0.00628 +0.91490 0.00613 +0.91961 0.00595 +0.92425 0.00574 +0.92882 0.00550 +0.93333 0.00523 +0.93778 0.00494 +0.94216 0.00462 +0.94647 0.00428 +0.95072 0.00392 +0.95490 0.00355 +0.95902 0.00315 +0.96307 0.00275 +0.96706 0.00233 +0.97098 0.00189 +0.97484 0.00145 +0.97863 0.00099 +0.98235 0.00053 +0.98601 0.00005 +0.98961 -0.00044 +0.99314 -0.00094 +0.99660 -0.00143 +1.00000 -0.00194 diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU25_A17.dat b/examples/NREL_5MW_Monopile/Airfoils/DU25_A17.dat new file mode 100644 index 0000000..60730d0 --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU25_A17.dat @@ -0,0 +1,194 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU25 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU25_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -3.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 8.5 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -8.5 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.4336 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.6873 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.006 Cd0 ! 2D drag coefficient value at 0-lift. + -0.12 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 140 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0202 0.0000 + -175.00 0.368 0.0324 0.1845 + -170.00 0.735 0.0943 0.3701 + -160.00 0.695 0.2848 0.2679 + -155.00 0.777 0.4001 0.3046 + -150.00 0.828 0.5215 0.3329 + -145.00 0.850 0.6447 0.3540 + -140.00 0.846 0.7660 0.3693 + -135.00 0.818 0.8823 0.3794 + -130.00 0.771 0.9911 0.3854 + -125.00 0.705 1.0905 0.3878 + -120.00 0.624 1.1787 0.3872 + -115.00 0.530 1.2545 0.3841 + -110.00 0.426 1.3168 0.3788 + -105.00 0.314 1.3650 0.3716 + -100.00 0.195 1.3984 0.3629 + -95.00 0.073 1.4169 0.3529 + -90.00 -0.050 1.4201 0.3416 + -85.00 -0.173 1.4081 0.3292 + -80.00 -0.294 1.3811 0.3159 + -75.00 -0.409 1.3394 0.3017 + -70.00 -0.518 1.2833 0.2866 + -65.00 -0.617 1.2138 0.2707 + -60.00 -0.706 1.1315 0.2539 + -55.00 -0.780 1.0378 0.2364 + -50.00 -0.839 0.9341 0.2181 + -45.00 -0.879 0.8221 0.1991 + -40.00 -0.898 0.7042 0.1792 + -35.00 -0.893 0.5829 0.1587 + -30.00 -0.862 0.4616 0.1374 + -25.00 -0.803 0.3441 0.1154 + -24.00 -0.792 0.3209 0.1101 + -23.00 -0.789 0.2972 0.1031 + -22.00 -0.792 0.2730 0.0947 + -21.00 -0.801 0.2485 0.0849 + -20.00 -0.815 0.2237 0.0739 + -19.00 -0.833 0.1990 0.0618 + -18.00 -0.854 0.1743 0.0488 + -17.00 -0.879 0.1498 0.0351 + -16.00 -0.905 0.1256 0.0208 + -15.00 -0.932 0.1020 0.0060 + -14.00 -0.959 0.0789 -0.0091 + -13.00 -0.985 0.0567 -0.0243 + -12.01 -0.953 0.0271 -0.0349 + -11.00 -0.900 0.0303 -0.0361 + -9.98 -0.827 0.0287 -0.0464 + -8.98 -0.753 0.0271 -0.0534 + -8.47 -0.691 0.0264 -0.0650 + -7.45 -0.555 0.0114 -0.0782 + -6.42 -0.413 0.0094 -0.0904 + -5.40 -0.271 0.0086 -0.1006 + -5.00 -0.220 0.0073 -0.1107 + -4.50 -0.152 0.0071 -0.1135 + -4.00 -0.084 0.0070 -0.1162 + -3.50 -0.018 0.0069 -0.1186 + -3.00 0.049 0.0068 -0.1209 + -2.50 0.115 0.0068 -0.1231 + -2.00 0.181 0.0068 -0.1252 + -1.50 0.247 0.0067 -0.1272 + -1.00 0.312 0.0067 -0.1293 + -0.50 0.377 0.0067 -0.1311 + 0.00 0.444 0.0065 -0.1330 + 0.50 0.508 0.0065 -0.1347 + 1.00 0.573 0.0066 -0.1364 + 1.50 0.636 0.0067 -0.1380 + 2.00 0.701 0.0068 -0.1396 + 2.50 0.765 0.0069 -0.1411 + 3.00 0.827 0.0070 -0.1424 + 3.50 0.890 0.0071 -0.1437 + 4.00 0.952 0.0073 -0.1448 + 4.50 1.013 0.0076 -0.1456 + 5.00 1.062 0.0079 -0.1445 + 6.00 1.161 0.0099 -0.1419 + 6.50 1.208 0.0117 -0.1403 + 7.00 1.254 0.0132 -0.1382 + 7.50 1.301 0.0143 -0.1362 + 8.00 1.336 0.0153 -0.1320 + 8.50 1.369 0.0165 -0.1276 + 9.00 1.400 0.0181 -0.1234 + 9.50 1.428 0.0211 -0.1193 + 10.00 1.442 0.0262 -0.1152 + 10.50 1.427 0.0336 -0.1115 + 11.00 1.374 0.0420 -0.1081 + 11.50 1.316 0.0515 -0.1052 + 12.00 1.277 0.0601 -0.1026 + 12.50 1.250 0.0693 -0.1000 + 13.00 1.246 0.0785 -0.0980 + 13.50 1.247 0.0888 -0.0969 + 14.00 1.256 0.1000 -0.0968 + 14.50 1.260 0.1108 -0.0973 + 15.00 1.271 0.1219 -0.0981 + 15.50 1.281 0.1325 -0.0992 + 16.00 1.289 0.1433 -0.1006 + 16.50 1.294 0.1541 -0.1023 + 17.00 1.304 0.1649 -0.1042 + 17.50 1.309 0.1754 -0.1064 + 18.00 1.315 0.1845 -0.1082 + 18.50 1.320 0.1953 -0.1110 + 19.00 1.330 0.2061 -0.1143 + 19.50 1.343 0.2170 -0.1179 + 20.00 1.354 0.2280 -0.1219 + 20.50 1.359 0.2390 -0.1261 + 21.00 1.360 0.2536 -0.1303 + 22.00 1.325 0.2814 -0.1375 + 23.00 1.288 0.3098 -0.1446 + 24.00 1.251 0.3386 -0.1515 + 25.00 1.215 0.3678 -0.1584 + 26.00 1.181 0.3972 -0.1651 + 28.00 1.120 0.4563 -0.1781 + 30.00 1.076 0.5149 -0.1904 + 32.00 1.056 0.5720 -0.2017 + 35.00 1.066 0.6548 -0.2173 + 40.00 1.064 0.7901 -0.2418 + 45.00 1.035 0.9190 -0.2650 + 50.00 0.980 1.0378 -0.2867 + 55.00 0.904 1.1434 -0.3072 + 60.00 0.810 1.2333 -0.3265 + 65.00 0.702 1.3055 -0.3446 + 70.00 0.582 1.3587 -0.3616 + 75.00 0.456 1.3922 -0.3775 + 80.00 0.326 1.4063 -0.3921 + 85.00 0.197 1.4042 -0.4057 + 90.00 0.072 1.3985 -0.4180 + 95.00 -0.050 1.3973 -0.4289 + 100.00 -0.170 1.3810 -0.4385 + 105.00 -0.287 1.3498 -0.4464 + 110.00 -0.399 1.3041 -0.4524 + 115.00 -0.502 1.2442 -0.4563 + 120.00 -0.596 1.1709 -0.4577 + 125.00 -0.677 1.0852 -0.4563 + 130.00 -0.743 0.9883 -0.4514 + 135.00 -0.792 0.8818 -0.4425 + 140.00 -0.821 0.7676 -0.4288 + 145.00 -0.826 0.6481 -0.4095 + 150.00 -0.806 0.5264 -0.3836 + 155.00 -0.758 0.4060 -0.3497 + 160.00 -0.679 0.2912 -0.3065 + 170.00 -0.735 0.0995 -0.3706 + 175.00 -0.368 0.0356 -0.1846 + 180.00 0.000 0.0202 0.0000 diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU25_A17_coords.txt b/examples/NREL_5MW_Monopile/Airfoils/DU25_A17_coords.txt new file mode 100644 index 0000000..8e481fb --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU25_A17_coords.txt @@ -0,0 +1,407 @@ + 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! DU 91-W2-250.lm +! x/c y/c +1.00000 0.00213 +0.99660 0.00314 +0.99314 0.00414 +0.98961 0.00515 +0.98601 0.00617 +0.98235 0.00720 +0.97863 0.00822 +0.97484 0.00926 +0.97098 0.01030 +0.96706 0.01135 +0.96307 0.01240 +0.95902 0.01347 +0.95490 0.01454 +0.95072 0.01562 +0.94647 0.01672 +0.94216 0.01783 +0.93778 0.01895 +0.93333 0.02009 +0.92882 0.02125 +0.92425 0.02241 +0.91961 0.02359 +0.91490 0.02479 +0.91013 0.02600 +0.90529 0.02722 +0.90039 0.02846 +0.89542 0.02972 +0.89039 0.03099 +0.88529 0.03227 +0.88013 0.03357 +0.87490 0.03489 +0.86961 0.03622 +0.86425 0.03756 +0.85882 0.03892 +0.85333 0.04029 +0.84778 0.04167 +0.84216 0.04306 +0.83647 0.04447 +0.83072 0.04589 +0.82490 0.04732 +0.81902 0.04877 +0.81307 0.05023 +0.80706 0.05170 +0.80098 0.05319 +0.79484 0.05468 +0.78863 0.05619 +0.78235 0.05771 +0.77601 0.05925 +0.76961 0.06078 +0.76314 0.06233 +0.75660 0.06388 +0.75000 0.06544 +0.74333 0.06701 +0.73667 0.06857 +0.73000 0.07013 +0.72333 0.07168 +0.71667 0.07322 +0.71000 0.07475 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0.12785 +0.31000 0.12749 +0.30333 0.12705 +0.29667 0.12656 +0.29000 0.12600 +0.28333 0.12538 +0.27667 0.12469 +0.27000 0.12394 +0.26333 0.12312 +0.25667 0.12224 +0.25000 0.12130 +0.24342 0.12030 +0.23693 0.11926 +0.23053 0.11817 +0.22421 0.11704 +0.21798 0.11586 +0.21184 0.11465 +0.20579 0.11340 +0.19982 0.11210 +0.19395 0.11078 +0.18816 0.10942 +0.18245 0.10803 +0.17684 0.10660 +0.17131 0.10515 +0.16587 0.10367 +0.16052 0.10217 +0.15526 0.10064 +0.15008 0.09909 +0.14499 0.09751 +0.13999 0.09591 +0.13508 0.09430 +0.13026 0.09266 +0.12552 0.09101 +0.12087 0.08934 +0.11631 0.08765 +0.11183 0.08595 +0.10745 0.08424 +0.10315 0.08251 +0.09893 0.08076 +0.09481 0.07902 +0.09077 0.07725 +0.08683 0.07549 +0.08297 0.07371 +0.07919 0.07192 +0.07551 0.07013 +0.07191 0.06834 +0.06840 0.06654 +0.06498 0.06474 +0.06164 0.06293 +0.05840 0.06113 +0.05524 0.05933 +0.05217 0.05753 +0.04918 0.05573 +0.04629 0.05393 +0.04348 0.05214 +0.04076 0.05035 +0.03812 0.04856 +0.03558 0.04679 +0.03312 0.04502 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+0.71000 -0.02456 +0.71667 -0.02238 +0.72333 -0.02026 +0.73000 -0.01817 +0.73667 -0.01614 +0.74333 -0.01416 +0.75000 -0.01223 +0.75660 -0.01038 +0.76314 -0.00861 +0.76961 -0.00692 +0.77601 -0.00532 +0.78235 -0.00381 +0.78863 -0.00238 +0.79484 -0.00103 +0.80098 0.00023 +0.80706 0.00141 +0.81307 0.00250 +0.81902 0.00351 +0.82490 0.00444 +0.83072 0.00529 +0.83647 0.00606 +0.84216 0.00675 +0.84778 0.00737 +0.85333 0.00791 +0.85882 0.00839 +0.86425 0.00879 +0.86961 0.00913 +0.87490 0.00940 +0.88013 0.00961 +0.88529 0.00975 +0.89039 0.00983 +0.89542 0.00985 +0.90039 0.00982 +0.90529 0.00972 +0.91013 0.00957 +0.91490 0.00936 +0.91961 0.00910 +0.92425 0.00880 +0.92882 0.00844 +0.93333 0.00804 +0.93778 0.00760 +0.94216 0.00712 +0.94647 0.00660 +0.95072 0.00606 +0.95490 0.00549 +0.95902 0.00490 +0.96307 0.00429 +0.96706 0.00367 +0.97098 0.00303 +0.97484 0.00238 +0.97863 0.00173 +0.98235 0.00108 +0.98601 0.00043 +0.98961 -0.00022 +0.99314 -0.00086 +0.99660 -0.00149 +1.00000 -0.00213 diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU30_A17.dat b/examples/NREL_5MW_Monopile/Airfoils/DU30_A17.dat new file mode 100644 index 0000000..438015c --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU30_A17.dat @@ -0,0 +1,198 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU30 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU30_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -2.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.449 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.6138 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.008 Cd0 ! 2D drag coefficient value at 0-lift. + -0.09 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 143 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0267 0.0000 + -175.00 0.274 0.0370 0.1379 + -170.00 0.547 0.0968 0.2778 + -160.00 0.685 0.2876 0.2740 + -155.00 0.766 0.4025 0.3118 + -150.00 0.816 0.5232 0.3411 + -145.00 0.836 0.6454 0.3631 + -140.00 0.832 0.7656 0.3791 + -135.00 0.804 0.8807 0.3899 + -130.00 0.756 0.9882 0.3965 + -125.00 0.690 1.0861 0.3994 + -120.00 0.609 1.1730 0.3992 + -115.00 0.515 1.2474 0.3964 + -110.00 0.411 1.3084 0.3915 + -105.00 0.300 1.3552 0.3846 + -100.00 0.182 1.3875 0.3761 + -95.00 0.061 1.4048 0.3663 + -90.00 -0.061 1.4070 0.3551 + -85.00 -0.183 1.3941 0.3428 + -80.00 -0.302 1.3664 0.3295 + -75.00 -0.416 1.3240 0.3153 + -70.00 -0.523 1.2676 0.3001 + -65.00 -0.622 1.1978 0.2841 + -60.00 -0.708 1.1156 0.2672 + -55.00 -0.781 1.0220 0.2494 + -50.00 -0.838 0.9187 0.2308 + -45.00 -0.877 0.8074 0.2113 + -40.00 -0.895 0.6904 0.1909 + -35.00 -0.889 0.5703 0.1696 + -30.00 -0.858 0.4503 0.1475 + -25.00 -0.832 0.3357 0.1224 + -24.00 -0.852 0.3147 0.1156 + -23.00 -0.882 0.2946 0.1081 + -22.00 -0.919 0.2752 0.1000 + -21.00 -0.963 0.2566 0.0914 + -20.00 -1.013 0.2388 0.0823 + -19.00 -1.067 0.2218 0.0728 + -18.00 -1.125 0.2056 0.0631 + -17.00 -1.185 0.1901 0.0531 + -16.00 -1.245 0.1754 0.0430 + -15.25 -1.290 0.1649 0.0353 + -14.24 -1.229 0.1461 0.0240 + -13.24 -1.148 0.1263 0.0100 + -12.22 -1.052 0.1051 -0.0090 + -11.22 -0.965 0.0886 -0.0230 + -10.19 -0.867 0.0740 -0.0336 + -9.70 -0.822 0.0684 -0.0375 + -9.18 -0.769 0.0605 -0.0440 + -8.18 -0.756 0.0270 -0.0578 + -7.19 -0.690 0.0180 -0.0590 + -6.65 -0.616 0.0166 -0.0633 + -6.13 -0.542 0.0152 -0.0674 + -6.00 -0.525 0.0117 -0.0732 + -5.50 -0.451 0.0105 -0.0766 + -5.00 -0.382 0.0097 -0.0797 + -4.50 -0.314 0.0092 -0.0825 + -4.00 -0.251 0.0091 -0.0853 + -3.50 -0.189 0.0089 -0.0884 + -3.00 -0.120 0.0089 -0.0914 + -2.50 -0.051 0.0088 -0.0942 + -2.00 0.017 0.0088 -0.0969 + -1.50 0.085 0.0088 -0.0994 + -1.00 0.152 0.0088 -0.1018 + -0.50 0.219 0.0088 -0.1041 + 0.00 0.288 0.0087 -0.1062 + 0.50 0.354 0.0087 -0.1086 + 1.00 0.421 0.0088 -0.1107 + 1.50 0.487 0.0089 -0.1129 + 2.00 0.554 0.0090 -0.1149 + 2.50 0.619 0.0091 -0.1168 + 3.00 0.685 0.0092 -0.1185 + 3.50 0.749 0.0093 -0.1201 + 4.00 0.815 0.0095 -0.1218 + 4.50 0.879 0.0096 -0.1233 + 5.00 0.944 0.0097 -0.1248 + 5.50 1.008 0.0099 -0.1260 + 6.00 1.072 0.0101 -0.1270 + 6.50 1.135 0.0103 -0.1280 + 7.00 1.197 0.0107 -0.1287 + 7.50 1.256 0.0112 -0.1289 + 8.00 1.305 0.0125 -0.1270 + 9.00 1.390 0.0155 -0.1207 + 9.50 1.424 0.0171 -0.1158 + 10.00 1.458 0.0192 -0.1116 + 10.50 1.488 0.0219 -0.1073 + 11.00 1.512 0.0255 -0.1029 + 11.50 1.533 0.0307 -0.0983 + 12.00 1.549 0.0370 -0.0949 + 12.50 1.558 0.0452 -0.0921 + 13.00 1.470 0.0630 -0.0899 + 13.50 1.398 0.0784 -0.0885 + 14.00 1.354 0.0931 -0.0885 + 14.50 1.336 0.1081 -0.0902 + 15.00 1.333 0.1239 -0.0928 + 15.50 1.326 0.1415 -0.0963 + 16.00 1.329 0.1592 -0.1006 + 16.50 1.326 0.1743 -0.1042 + 17.00 1.321 0.1903 -0.1084 + 17.50 1.331 0.2044 -0.1125 + 18.00 1.333 0.2186 -0.1169 + 18.50 1.340 0.2324 -0.1215 + 19.00 1.362 0.2455 -0.1263 + 19.50 1.382 0.2584 -0.1313 + 20.00 1.398 0.2689 -0.1352 + 20.50 1.426 0.2814 -0.1406 + 21.00 1.437 0.2943 -0.1462 + 22.00 1.418 0.3246 -0.1516 + 23.00 1.397 0.3557 -0.1570 + 24.00 1.376 0.3875 -0.1623 + 25.00 1.354 0.4198 -0.1676 + 26.00 1.332 0.4524 -0.1728 + 28.00 1.293 0.5183 -0.1832 + 30.00 1.265 0.5843 -0.1935 + 32.00 1.253 0.6492 -0.2039 + 35.00 1.264 0.7438 -0.2193 + 40.00 1.258 0.8970 -0.2440 + 45.00 1.217 1.0402 -0.2672 + 50.00 1.146 1.1686 -0.2891 + 55.00 1.049 1.2779 -0.3097 + 60.00 0.932 1.3647 -0.3290 + 65.00 0.799 1.4267 -0.3471 + 70.00 0.657 1.4621 -0.3641 + 75.00 0.509 1.4708 -0.3799 + 80.00 0.362 1.4544 -0.3946 + 85.00 0.221 1.4196 -0.4081 + 90.00 0.092 1.3938 -0.4204 + 95.00 -0.030 1.3943 -0.4313 + 100.00 -0.150 1.3798 -0.4408 + 105.00 -0.267 1.3504 -0.4486 + 110.00 -0.379 1.3063 -0.4546 + 115.00 -0.483 1.2481 -0.4584 + 120.00 -0.578 1.1763 -0.4597 + 125.00 -0.660 1.0919 -0.4582 + 130.00 -0.727 0.9962 -0.4532 + 135.00 -0.777 0.8906 -0.4441 + 140.00 -0.807 0.7771 -0.4303 + 145.00 -0.815 0.6581 -0.4109 + 150.00 -0.797 0.5364 -0.3848 + 155.00 -0.750 0.4157 -0.3508 + 160.00 -0.673 0.3000 -0.3074 + 170.00 -0.547 0.1051 -0.2786 + 175.00 -0.274 0.0388 -0.1380 + 180.00 0.000 0.0267 0.0000 + diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU30_A17_coords.txt b/examples/NREL_5MW_Monopile/Airfoils/DU30_A17_coords.txt new file mode 100644 index 0000000..722bf83 --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU30_A17_coords.txt @@ -0,0 +1,407 @@ + 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! DU 97-W-300.lm +! x/c y/c +1.00000 0.00246 +0.99660 0.00340 +0.99314 0.00437 +0.98961 0.00536 +0.98601 0.00638 +0.98235 0.00740 +0.97863 0.00843 +0.97484 0.00947 +0.97098 0.01051 +0.96706 0.01157 +0.96307 0.01264 +0.95902 0.01371 +0.95490 0.01479 +0.95072 0.01588 +0.94647 0.01698 +0.94216 0.01810 +0.93778 0.01922 +0.93333 0.02036 +0.92882 0.02151 +0.92425 0.02268 +0.91961 0.02386 +0.91490 0.02505 +0.91013 0.02626 +0.90529 0.02749 +0.90039 0.02873 +0.89542 0.02999 +0.89039 0.03126 +0.88529 0.03255 +0.88013 0.03385 +0.87490 0.03516 +0.86961 0.03649 +0.86425 0.03784 +0.85882 0.03921 +0.85333 0.04058 +0.84778 0.04197 +0.84216 0.04337 +0.83647 0.04479 +0.83072 0.04622 +0.82490 0.04767 +0.81902 0.04913 +0.81307 0.05060 +0.80706 0.05208 +0.80098 0.05357 +0.79484 0.05508 +0.78863 0.05659 +0.78235 0.05812 +0.77601 0.05965 +0.76961 0.06120 +0.76314 0.06275 +0.75660 0.06432 +0.75000 0.06589 +0.74333 0.06747 +0.73667 0.06904 +0.73000 0.07061 +0.72333 0.07217 +0.71667 0.07371 +0.71000 0.07525 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0.13420 +0.31000 0.13424 +0.30333 0.13422 +0.29667 0.13415 +0.29000 0.13401 +0.28333 0.13381 +0.27667 0.13355 +0.27000 0.13321 +0.26333 0.13280 +0.25667 0.13231 +0.25000 0.13174 +0.24342 0.13109 +0.23693 0.13036 +0.23053 0.12955 +0.22421 0.12866 +0.21798 0.12771 +0.21184 0.12668 +0.20579 0.12559 +0.19982 0.12444 +0.19395 0.12324 +0.18816 0.12197 +0.18245 0.12066 +0.17684 0.11930 +0.17131 0.11789 +0.16587 0.11644 +0.16052 0.11495 +0.15526 0.11342 +0.15008 0.11185 +0.14499 0.11024 +0.13999 0.10860 +0.13508 0.10693 +0.13026 0.10522 +0.12552 0.10348 +0.12087 0.10172 +0.11631 0.09993 +0.11183 0.09811 +0.10745 0.09627 +0.10315 0.09441 +0.09893 0.09252 +0.09481 0.09061 +0.09077 0.08869 +0.08683 0.08675 +0.08297 0.08478 +0.07919 0.08280 +0.07551 0.08082 +0.07191 0.07881 +0.06840 0.07680 +0.06498 0.07477 +0.06164 0.07274 +0.05840 0.07070 +0.05524 0.06865 +0.05217 0.06660 +0.04918 0.06454 +0.04629 0.06248 +0.04348 0.06042 +0.04076 0.05835 +0.03812 0.05629 +0.03558 0.05423 +0.03312 0.05217 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+0.71000 -0.03931 +0.71667 -0.03703 +0.72333 -0.03478 +0.73000 -0.03256 +0.73667 -0.03037 +0.74333 -0.02822 +0.75000 -0.02610 +0.75660 -0.02405 +0.76314 -0.02205 +0.76961 -0.02013 +0.77601 -0.01827 +0.78235 -0.01647 +0.78863 -0.01474 +0.79484 -0.01309 +0.80098 -0.01150 +0.80706 -0.00998 +0.81307 -0.00854 +0.81902 -0.00717 +0.82490 -0.00586 +0.83072 -0.00462 +0.83647 -0.00346 +0.84216 -0.00236 +0.84778 -0.00133 +0.85333 -0.00037 +0.85882 0.00052 +0.86425 0.00134 +0.86961 0.00210 +0.87490 0.00278 +0.88013 0.00340 +0.88529 0.00395 +0.89039 0.00444 +0.89542 0.00487 +0.90039 0.00524 +0.90529 0.00555 +0.91013 0.00580 +0.91490 0.00600 +0.91961 0.00614 +0.92425 0.00622 +0.92882 0.00625 +0.93333 0.00623 +0.93778 0.00615 +0.94216 0.00602 +0.94647 0.00583 +0.95072 0.00558 +0.95490 0.00528 +0.95902 0.00493 +0.96307 0.00452 +0.96706 0.00405 +0.97098 0.00352 +0.97484 0.00294 +0.97863 0.00231 +0.98235 0.00163 +0.98601 0.00090 +0.98961 0.00012 +0.99314 -0.00071 +0.99660 -0.00158 +1.00000 -0.00246 diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU35_A17.dat b/examples/NREL_5MW_Monopile/Airfoils/DU35_A17.dat new file mode 100644 index 0000000..48e2b5f --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU35_A17.dat @@ -0,0 +1,189 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU35 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU35_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -1.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 11.5 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -11.5 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.6717 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.3075 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.012 Cd0 ! 2D drag coefficient value at 0-lift. + -0.07 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 135 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0407 0.0000 + -175.00 0.223 0.0507 0.0937 + -170.00 0.405 0.1055 0.1702 + -160.00 0.658 0.2982 0.2819 + -155.00 0.733 0.4121 0.3213 + -150.00 0.778 0.5308 0.3520 + -145.00 0.795 0.6503 0.3754 + -140.00 0.787 0.7672 0.3926 + -135.00 0.757 0.8785 0.4046 + -130.00 0.708 0.9819 0.4121 + -125.00 0.641 1.0756 0.4160 + -120.00 0.560 1.1580 0.4167 + -115.00 0.467 1.2280 0.4146 + -110.00 0.365 1.2847 0.4104 + -105.00 0.255 1.3274 0.4041 + -100.00 0.139 1.3557 0.3961 + -95.00 0.021 1.3692 0.3867 + -90.00 -0.098 1.3680 0.3759 + -85.00 -0.216 1.3521 0.3639 + -80.00 -0.331 1.3218 0.3508 + -75.00 -0.441 1.2773 0.3367 + -70.00 -0.544 1.2193 0.3216 + -65.00 -0.638 1.1486 0.3054 + -60.00 -0.720 1.0660 0.2884 + -55.00 -0.788 0.9728 0.2703 + -50.00 -0.840 0.8705 0.2512 + -45.00 -0.875 0.7611 0.2311 + -40.00 -0.889 0.6466 0.2099 + -35.00 -0.880 0.5299 0.1876 + -30.00 -0.846 0.4141 0.1641 + -25.00 -0.784 0.3030 0.1396 + -24.00 -0.768 0.2817 0.1345 + -23.00 -0.751 0.2608 0.1294 + -22.00 -0.733 0.2404 0.1243 + -21.00 -0.714 0.2205 0.1191 + -20.00 -0.693 0.2011 0.1139 + -19.00 -0.671 0.1822 0.1086 + -18.00 -0.648 0.1640 0.1032 + -17.00 -0.624 0.1465 0.0975 + -16.00 -0.601 0.1300 0.0898 + -15.00 -0.579 0.1145 0.0799 + -14.00 -0.559 0.1000 0.0682 + -13.00 -0.539 0.0867 0.0547 + -12.00 -0.519 0.0744 0.0397 + -11.00 -0.499 0.0633 0.0234 + -10.00 -0.480 0.0534 0.0060 + -5.54 -0.385 0.0245 -0.0800 + -5.04 -0.359 0.0225 -0.0800 + -4.54 -0.360 0.0196 -0.0800 + -4.04 -0.355 0.0174 -0.0800 + -3.54 -0.307 0.0162 -0.0800 + -3.04 -0.246 0.0144 -0.0800 + -3.00 -0.240 0.0240 -0.0623 + -2.50 -0.163 0.0188 -0.0674 + -2.00 -0.091 0.0160 -0.0712 + -1.50 -0.019 0.0137 -0.0746 + -1.00 0.052 0.0118 -0.0778 + -0.50 0.121 0.0104 -0.0806 + 0.00 0.196 0.0094 -0.0831 + 0.50 0.265 0.0096 -0.0863 + 1.00 0.335 0.0098 -0.0895 + 1.50 0.404 0.0099 -0.0924 + 2.00 0.472 0.0100 -0.0949 + 2.50 0.540 0.0102 -0.0973 + 3.00 0.608 0.0103 -0.0996 + 3.50 0.674 0.0104 -0.1016 + 4.00 0.742 0.0105 -0.1037 + 4.50 0.809 0.0107 -0.1057 + 5.00 0.875 0.0108 -0.1076 + 5.50 0.941 0.0109 -0.1094 + 6.00 1.007 0.0110 -0.1109 + 6.50 1.071 0.0113 -0.1118 + 7.00 1.134 0.0115 -0.1127 + 7.50 1.198 0.0117 -0.1138 + 8.00 1.260 0.0120 -0.1144 + 8.50 1.318 0.0126 -0.1137 + 9.00 1.368 0.0133 -0.1112 + 9.50 1.422 0.0143 -0.1100 + 10.00 1.475 0.0156 -0.1086 + 10.50 1.523 0.0174 -0.1064 + 11.00 1.570 0.0194 -0.1044 + 11.50 1.609 0.0227 -0.1013 + 12.00 1.642 0.0269 -0.0980 + 12.50 1.675 0.0319 -0.0953 + 13.00 1.700 0.0398 -0.0925 + 13.50 1.717 0.0488 -0.0896 + 14.00 1.712 0.0614 -0.0864 + 14.50 1.703 0.0786 -0.0840 + 15.50 1.671 0.1173 -0.0830 + 16.00 1.649 0.1377 -0.0848 + 16.50 1.621 0.1600 -0.0880 + 17.00 1.598 0.1814 -0.0926 + 17.50 1.571 0.2042 -0.0984 + 18.00 1.549 0.2316 -0.1052 + 19.00 1.544 0.2719 -0.1158 + 19.50 1.549 0.2906 -0.1213 + 20.00 1.565 0.3085 -0.1248 + 21.00 1.565 0.3447 -0.1317 + 22.00 1.563 0.3820 -0.1385 + 23.00 1.558 0.4203 -0.1452 + 24.00 1.552 0.4593 -0.1518 + 25.00 1.546 0.4988 -0.1583 + 26.00 1.539 0.5387 -0.1647 + 28.00 1.527 0.6187 -0.1770 + 30.00 1.522 0.6978 -0.1886 + 32.00 1.529 0.7747 -0.1994 + 35.00 1.544 0.8869 -0.2148 + 40.00 1.529 1.0671 -0.2392 + 45.00 1.471 1.2319 -0.2622 + 50.00 1.376 1.3747 -0.2839 + 55.00 1.249 1.4899 -0.3043 + 60.00 1.097 1.5728 -0.3236 + 65.00 0.928 1.6202 -0.3417 + 70.00 0.750 1.6302 -0.3586 + 75.00 0.570 1.6031 -0.3745 + 80.00 0.396 1.5423 -0.3892 + 85.00 0.237 1.4598 -0.4028 + 90.00 0.101 1.4041 -0.4151 + 95.00 -0.022 1.4053 -0.4261 + 100.00 -0.143 1.3914 -0.4357 + 105.00 -0.261 1.3625 -0.4437 + 110.00 -0.374 1.3188 -0.4498 + 115.00 -0.480 1.2608 -0.4538 + 120.00 -0.575 1.1891 -0.4553 + 125.00 -0.659 1.1046 -0.4540 + 130.00 -0.727 1.0086 -0.4492 + 135.00 -0.778 0.9025 -0.4405 + 140.00 -0.809 0.7883 -0.4270 + 145.00 -0.818 0.6684 -0.4078 + 150.00 -0.800 0.5457 -0.3821 + 155.00 -0.754 0.4236 -0.3484 + 160.00 -0.677 0.3066 -0.3054 + 170.00 -0.417 0.1085 -0.1842 + 175.00 -0.229 0.0510 -0.1013 + 180.00 0.000 0.0407 0.0000 diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU35_A17_coords.txt b/examples/NREL_5MW_Monopile/Airfoils/DU35_A17_coords.txt new file mode 100644 index 0000000..5d3f84e --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU35_A17_coords.txt @@ -0,0 +1,407 @@ + 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! Adjusted DU 35 +! x/c y/c +1.00000 0.00283 +0.99660 0.00378 +0.99314 0.00477 +0.98961 0.00578 +0.98601 0.00683 +0.98235 0.00789 +0.97863 0.00897 +0.97484 0.01006 +0.97098 0.01116 +0.96706 0.01228 +0.96307 0.01342 +0.95902 0.01456 +0.95490 0.01571 +0.95072 0.01688 +0.94647 0.01806 +0.94216 0.01926 +0.93778 0.02046 +0.93333 0.02169 +0.92882 0.02292 +0.92425 0.02419 +0.91961 0.02547 +0.91490 0.02675 +0.91013 0.02807 +0.90529 0.02941 +0.90039 0.03077 +0.89542 0.03214 +0.89039 0.03353 +0.88529 0.03495 +0.88013 0.03638 +0.87490 0.03782 +0.86961 0.03929 +0.86425 0.04079 +0.85882 0.04230 +0.85333 0.04383 +0.84778 0.04538 +0.84216 0.04694 +0.83647 0.04853 +0.83072 0.05013 +0.82490 0.05176 +0.81902 0.05340 +0.81307 0.05506 +0.80706 0.05673 +0.80098 0.05842 +0.79484 0.06013 +0.78863 0.06184 +0.78235 0.06358 +0.77601 0.06531 +0.76961 0.06708 +0.76314 0.06885 +0.75660 0.07064 +0.75000 0.07244 +0.74333 0.07426 +0.73667 0.07606 +0.73000 0.07786 +0.72333 0.07966 +0.71667 0.08144 +0.71000 0.08322 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-0.00283 diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU40_A17.dat b/examples/NREL_5MW_Monopile/Airfoils/DU40_A17.dat new file mode 100644 index 0000000..54a6d4a --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU40_A17.dat @@ -0,0 +1,190 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU40 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU40_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -3.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.3519 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.3226 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.03 Cd0 ! 2D drag coefficient value at 0-lift. + -0.05 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 136 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0602 0.0000 + -175.00 0.218 0.0699 0.0934 + -170.00 0.397 0.1107 0.1697 + -160.00 0.642 0.3045 0.2813 + -155.00 0.715 0.4179 0.3208 + -150.00 0.757 0.5355 0.3516 + -145.00 0.772 0.6535 0.3752 + -140.00 0.762 0.7685 0.3926 + -135.00 0.731 0.8777 0.4048 + -130.00 0.680 0.9788 0.4126 + -125.00 0.613 1.0700 0.4166 + -120.00 0.532 1.1499 0.4176 + -115.00 0.439 1.2174 0.4158 + -110.00 0.337 1.2716 0.4117 + -105.00 0.228 1.3118 0.4057 + -100.00 0.114 1.3378 0.3979 + -95.00 -0.002 1.3492 0.3887 + -90.00 -0.120 1.3460 0.3781 + -85.00 -0.236 1.3283 0.3663 + -80.00 -0.349 1.2964 0.3534 + -75.00 -0.456 1.2507 0.3394 + -70.00 -0.557 1.1918 0.3244 + -65.00 -0.647 1.1204 0.3084 + -60.00 -0.727 1.0376 0.2914 + -55.00 -0.792 0.9446 0.2733 + -50.00 -0.842 0.8429 0.2543 + -45.00 -0.874 0.7345 0.2342 + -40.00 -0.886 0.6215 0.2129 + -35.00 -0.875 0.5067 0.1906 + -30.00 -0.839 0.3932 0.1670 + -25.00 -0.777 0.2849 0.1422 + -24.00 -0.761 0.2642 0.1371 + -23.00 -0.744 0.2440 0.1320 + -22.00 -0.725 0.2242 0.1268 + -21.00 -0.706 0.2049 0.1215 + -20.00 -0.685 0.1861 0.1162 + -19.00 -0.662 0.1687 0.1097 + -18.00 -0.635 0.1533 0.1012 + -17.00 -0.605 0.1398 0.0907 + -16.00 -0.571 0.1281 0.0784 + -15.00 -0.534 0.1183 0.0646 + -14.00 -0.494 0.1101 0.0494 + -13.00 -0.452 0.1036 0.0330 + -12.00 -0.407 0.0986 0.0156 + -11.00 -0.360 0.0951 -0.0026 + -10.00 -0.311 0.0931 -0.0213 + -8.00 -0.208 0.0930 -0.0600 + -6.00 -0.111 0.0689 -0.0500 + -5.50 -0.090 0.0614 -0.0516 + -5.00 -0.072 0.0547 -0.0532 + -4.50 -0.065 0.0480 -0.0538 + -4.00 -0.054 0.0411 -0.0544 + -3.50 -0.017 0.0349 -0.0554 + -3.00 0.003 0.0299 -0.0558 + -2.50 0.014 0.0255 -0.0555 + -2.00 0.009 0.0198 -0.0534 + -1.50 0.004 0.0164 -0.0442 + -1.00 0.036 0.0147 -0.0469 + -0.50 0.073 0.0137 -0.0522 + 0.00 0.137 0.0113 -0.0573 + 0.50 0.213 0.0114 -0.0644 + 1.00 0.292 0.0118 -0.0718 + 1.50 0.369 0.0122 -0.0783 + 2.00 0.444 0.0124 -0.0835 + 2.50 0.514 0.0124 -0.0866 + 3.00 0.580 0.0123 -0.0887 + 3.50 0.645 0.0120 -0.0900 + 4.00 0.710 0.0119 -0.0914 + 4.50 0.776 0.0122 -0.0933 + 5.00 0.841 0.0125 -0.0947 + 5.50 0.904 0.0129 -0.0957 + 6.00 0.967 0.0135 -0.0967 + 6.50 1.027 0.0144 -0.0973 + 7.00 1.084 0.0158 -0.0972 + 7.50 1.140 0.0174 -0.0972 + 8.00 1.193 0.0198 -0.0968 + 8.50 1.242 0.0231 -0.0958 + 9.00 1.287 0.0275 -0.0948 + 9.50 1.333 0.0323 -0.0942 + 10.00 1.368 0.0393 -0.0926 + 10.50 1.400 0.0475 -0.0908 + 11.00 1.425 0.0580 -0.0890 + 11.50 1.449 0.0691 -0.0877 + 12.00 1.473 0.0816 -0.0870 + 12.50 1.494 0.0973 -0.0870 + 13.00 1.513 0.1129 -0.0876 + 13.50 1.538 0.1288 -0.0886 + 14.50 1.587 0.1650 -0.0917 + 15.00 1.614 0.1845 -0.0939 + 15.50 1.631 0.2052 -0.0966 + 16.00 1.649 0.2250 -0.0996 + 16.50 1.666 0.2467 -0.1031 + 17.00 1.681 0.2684 -0.1069 + 17.50 1.699 0.2900 -0.1110 + 18.00 1.719 0.3121 -0.1157 + 19.00 1.751 0.3554 -0.1242 + 19.50 1.767 0.3783 -0.1291 + 20.50 1.798 0.4212 -0.1384 + 21.00 1.810 0.4415 -0.1416 + 22.00 1.830 0.4830 -0.1479 + 23.00 1.847 0.5257 -0.1542 + 24.00 1.861 0.5694 -0.1603 + 25.00 1.872 0.6141 -0.1664 + 26.00 1.881 0.6593 -0.1724 + 28.00 1.894 0.7513 -0.1841 + 30.00 1.904 0.8441 -0.1954 + 32.00 1.915 0.9364 -0.2063 + 35.00 1.929 1.0722 -0.2220 + 40.00 1.903 1.2873 -0.2468 + 45.00 1.820 1.4796 -0.2701 + 50.00 1.690 1.6401 -0.2921 + 55.00 1.522 1.7609 -0.3127 + 60.00 1.323 1.8360 -0.3321 + 65.00 1.106 1.8614 -0.3502 + 70.00 0.880 1.8347 -0.3672 + 75.00 0.658 1.7567 -0.3830 + 80.00 0.449 1.6334 -0.3977 + 85.00 0.267 1.4847 -0.4112 + 90.00 0.124 1.3879 -0.4234 + 95.00 0.002 1.3912 -0.4343 + 100.00 -0.118 1.3795 -0.4437 + 105.00 -0.235 1.3528 -0.4514 + 110.00 -0.348 1.3114 -0.4573 + 115.00 -0.453 1.2557 -0.4610 + 120.00 -0.549 1.1864 -0.4623 + 125.00 -0.633 1.1041 -0.4606 + 130.00 -0.702 1.0102 -0.4554 + 135.00 -0.754 0.9060 -0.4462 + 140.00 -0.787 0.7935 -0.4323 + 145.00 -0.797 0.6750 -0.4127 + 150.00 -0.782 0.5532 -0.3863 + 155.00 -0.739 0.4318 -0.3521 + 160.00 -0.664 0.3147 -0.3085 + 170.00 -0.410 0.1144 -0.1858 + 175.00 -0.226 0.0702 -0.1022 + 180.00 0.000 0.0602 0.0000 diff --git a/examples/NREL_5MW_Monopile/Airfoils/DU40_A17_coords.txt b/examples/NREL_5MW_Monopile/Airfoils/DU40_A17_coords.txt new file mode 100644 index 0000000..18d11b7 --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/DU40_A17_coords.txt @@ -0,0 +1,407 @@ + 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c +0.33087 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! Adjusted DU4050 +! x/c y/c +1.00000 0.00347 +0.99660 0.00455 +0.99314 0.00565 +0.98961 0.00678 +0.98601 0.00795 +0.98235 0.00914 +0.97863 0.01035 +0.97484 0.01158 +0.97098 0.01283 +0.96706 0.01410 +0.96307 0.01539 +0.95902 0.01670 +0.95490 0.01803 +0.95072 0.01937 +0.94647 0.02074 +0.94216 0.02212 +0.93778 0.02352 +0.93333 0.02495 +0.92882 0.02639 +0.92425 0.02786 +0.91961 0.02936 +0.91490 0.03087 +0.91013 0.03242 +0.90529 0.03400 +0.90039 0.03560 +0.89542 0.03723 +0.89039 0.03887 +0.88529 0.04056 +0.88013 0.04226 +0.87490 0.04399 +0.86961 0.04575 +0.86425 0.04754 +0.85882 0.04935 +0.85333 0.05119 +0.84778 0.05305 +0.84216 0.05493 +0.83647 0.05685 +0.83072 0.05878 +0.82490 0.06076 +0.81902 0.06275 +0.81307 0.06476 +0.80706 0.06680 +0.80098 0.06886 +0.79484 0.07094 +0.78863 0.07304 +0.78235 0.07517 +0.77601 0.07730 +0.76961 0.07947 +0.76314 0.08165 +0.75660 0.08386 +0.75000 0.08608 +0.74333 0.08832 +0.73667 0.09056 +0.73000 0.09279 +0.72333 0.09502 +0.71667 0.09724 +0.71000 0.09946 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-0.00347 diff --git a/examples/NREL_5MW_Monopile/Airfoils/NACA64_A17.dat b/examples/NREL_5MW_Monopile/Airfoils/NACA64_A17.dat new file mode 100644 index 0000000..b9dca30 --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/NACA64_A17.dat @@ -0,0 +1,181 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA64 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA64_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -4.432 alpha0 ! 0-lift angle of attack, depends on airfoil. + 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.4073 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.7945 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.0065 Cd0 ! 2D drag coefficient value at 0-lift. + -0.088 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +"Default" x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"Default" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 127 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0198 0.0000 + -175.00 0.374 0.0341 0.1880 + -170.00 0.749 0.0955 0.3770 + -160.00 0.659 0.2807 0.2747 + -155.00 0.736 0.3919 0.3130 + -150.00 0.783 0.5086 0.3428 + -145.00 0.803 0.6267 0.3654 + -140.00 0.798 0.7427 0.3820 + -135.00 0.771 0.8537 0.3935 + -130.00 0.724 0.9574 0.4007 + -125.00 0.660 1.0519 0.4042 + -120.00 0.581 1.1355 0.4047 + -115.00 0.491 1.2070 0.4025 + -110.00 0.390 1.2656 0.3981 + -105.00 0.282 1.3104 0.3918 + -100.00 0.169 1.3410 0.3838 + -95.00 0.052 1.3572 0.3743 + -90.00 -0.067 1.3587 0.3636 + -85.00 -0.184 1.3456 0.3517 + -80.00 -0.299 1.3181 0.3388 + -75.00 -0.409 1.2765 0.3248 + -70.00 -0.512 1.2212 0.3099 + -65.00 -0.606 1.1532 0.2940 + -60.00 -0.689 1.0731 0.2772 + -55.00 -0.759 0.9822 0.2595 + -50.00 -0.814 0.8820 0.2409 + -45.00 -0.850 0.7742 0.2212 + -40.00 -0.866 0.6610 0.2006 + -35.00 -0.860 0.5451 0.1789 + -30.00 -0.829 0.4295 0.1563 + -25.00 -0.853 0.3071 0.1156 + -24.00 -0.870 0.2814 0.1040 + -23.00 -0.890 0.2556 0.0916 + -22.00 -0.911 0.2297 0.0785 + -21.00 -0.934 0.2040 0.0649 + -20.00 -0.958 0.1785 0.0508 + -19.00 -0.982 0.1534 0.0364 + -18.00 -1.005 0.1288 0.0218 + -17.00 -1.082 0.1037 0.0129 + -16.00 -1.113 0.0786 -0.0028 + -15.00 -1.105 0.0535 -0.0251 + -14.00 -1.078 0.0283 -0.0419 + -13.50 -1.053 0.0158 -0.0521 + -13.00 -1.015 0.0151 -0.0610 + -12.00 -0.904 0.0134 -0.0707 + -11.00 -0.807 0.0121 -0.0722 + -10.00 -0.711 0.0111 -0.0734 + -9.00 -0.595 0.0099 -0.0772 + -8.00 -0.478 0.0091 -0.0807 + -7.00 -0.375 0.0086 -0.0825 + -6.00 -0.264 0.0082 -0.0832 + -5.00 -0.151 0.0079 -0.0841 + -4.00 -0.017 0.0072 -0.0869 + -3.00 0.088 0.0064 -0.0912 + -2.00 0.213 0.0054 -0.0946 + -1.00 0.328 0.0052 -0.0971 + 0.00 0.442 0.0052 -0.1014 + 1.00 0.556 0.0052 -0.1076 + 2.00 0.670 0.0053 -0.1126 + 3.00 0.784 0.0053 -0.1157 + 4.00 0.898 0.0054 -0.1199 + 5.00 1.011 0.0058 -0.1240 + 6.00 1.103 0.0091 -0.1234 + 7.00 1.181 0.0113 -0.1184 + 8.00 1.257 0.0124 -0.1163 + 8.50 1.293 0.0130 -0.1163 + 9.00 1.326 0.0136 -0.1160 + 9.50 1.356 0.0143 -0.1154 + 10.00 1.382 0.0150 -0.1149 + 10.50 1.400 0.0267 -0.1145 + 11.00 1.415 0.0383 -0.1143 + 11.50 1.425 0.0498 -0.1147 + 12.00 1.434 0.0613 -0.1158 + 12.50 1.443 0.0727 -0.1165 + 13.00 1.451 0.0841 -0.1153 + 13.50 1.453 0.0954 -0.1131 + 14.00 1.448 0.1065 -0.1112 + 14.50 1.444 0.1176 -0.1101 + 15.00 1.445 0.1287 -0.1103 + 15.50 1.447 0.1398 -0.1109 + 16.00 1.448 0.1509 -0.1114 + 16.50 1.444 0.1619 -0.1111 + 17.00 1.438 0.1728 -0.1097 + 17.50 1.439 0.1837 -0.1079 + 18.00 1.448 0.1947 -0.1080 + 18.50 1.452 0.2057 -0.1090 + 19.00 1.448 0.2165 -0.1086 + 19.50 1.438 0.2272 -0.1077 + 20.00 1.428 0.2379 -0.1099 + 21.00 1.401 0.2590 -0.1169 + 22.00 1.359 0.2799 -0.1190 + 23.00 1.300 0.3004 -0.1235 + 24.00 1.220 0.3204 -0.1393 + 25.00 1.168 0.3377 -0.1440 + 26.00 1.116 0.3554 -0.1486 + 28.00 1.015 0.3916 -0.1577 + 30.00 0.926 0.4294 -0.1668 + 32.00 0.855 0.4690 -0.1759 + 35.00 0.800 0.5324 -0.1897 + 40.00 0.804 0.6452 -0.2126 + 45.00 0.793 0.7573 -0.2344 + 50.00 0.763 0.8664 -0.2553 + 55.00 0.717 0.9708 -0.2751 + 60.00 0.656 1.0693 -0.2939 + 65.00 0.582 1.1606 -0.3117 + 70.00 0.495 1.2438 -0.3285 + 75.00 0.398 1.3178 -0.3444 + 80.00 0.291 1.3809 -0.3593 + 85.00 0.176 1.4304 -0.3731 + 90.00 0.053 1.4565 -0.3858 + 95.00 -0.074 1.4533 -0.3973 + 100.00 -0.199 1.4345 -0.4075 + 105.00 -0.321 1.4004 -0.4162 + 110.00 -0.436 1.3512 -0.4231 + 115.00 -0.543 1.2874 -0.4280 + 120.00 -0.640 1.2099 -0.4306 + 125.00 -0.723 1.1196 -0.4304 + 130.00 -0.790 1.0179 -0.4270 + 135.00 -0.840 0.9064 -0.4196 + 140.00 -0.868 0.7871 -0.4077 + 145.00 -0.872 0.6627 -0.3903 + 150.00 -0.850 0.5363 -0.3665 + 155.00 -0.798 0.4116 -0.3349 + 160.00 -0.714 0.2931 -0.2942 + 170.00 -0.749 0.0971 -0.3771 + 175.00 -0.374 0.0334 -0.1879 + 180.00 0.000 0.0198 0.0000 diff --git a/examples/NREL_5MW_Monopile/Airfoils/NACA64_A17_coords.txt b/examples/NREL_5MW_Monopile/Airfoils/NACA64_A17_coords.txt new file mode 100644 index 0000000..b2b49e0 --- /dev/null +++ b/examples/NREL_5MW_Monopile/Airfoils/NACA64_A17_coords.txt @@ -0,0 +1,407 @@ + 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! NACA 64-618 (interpolated to 399 points) +! x/c y/c +1.000000 0.000000 +0.990000 0.003385 +0.980000 0.006126 +0.975000 0.007447 +0.970000 0.008767 +0.965000 0.010062 +0.960000 0.011357 +0.955000 0.012639 +0.950000 0.013921 +0.945000 0.015200 +0.940000 0.016478 +0.935000 0.017757 +0.930000 0.019036 +0.925000 0.020317 +0.920000 0.021598 +0.915000 0.022881 +0.910000 0.024163 +0.905000 0.025448 +0.900000 0.026733 +0.887500 0.029951 +0.875000 0.033169 +0.862500 0.036386 +0.850000 0.039603 +0.837500 0.042804 +0.825000 0.046004 +0.812500 0.049171 +0.800000 0.052337 +0.787500 0.055452 +0.775000 0.058566 +0.762500 0.061611 +0.750000 0.064656 +0.737500 0.067615 +0.725000 0.070573 +0.712500 0.073429 +0.700000 0.076285 +0.687500 0.079029 +0.675000 0.081773 +0.662500 0.084393 +0.650000 0.087012 +0.637500 0.089490 +0.625000 0.091967 +0.612500 0.094283 +0.600000 0.096599 +0.587500 0.098743 +0.575000 0.100887 +0.562500 0.102843 +0.550000 0.104799 +0.537500 0.106549 +0.525000 0.108299 +0.512500 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-0.036486 +0.612500 -0.034526 +0.625000 -0.032565 +0.637500 -0.030575 +0.650000 -0.028585 +0.662500 -0.026594 +0.675000 -0.024603 +0.687500 -0.022632 +0.700000 -0.020660 +0.712500 -0.018728 +0.725000 -0.016795 +0.737500 -0.014922 +0.750000 -0.013048 +0.762500 -0.011260 +0.775000 -0.009472 +0.787500 -0.007797 +0.800000 -0.006122 +0.812500 -0.004594 +0.825000 -0.003065 +0.837500 -0.001721 +0.850000 -0.000376 +0.862500 0.000742 +0.875000 0.001859 +0.887500 0.002698 +0.900000 0.003536 +0.905000 0.003780 +0.910000 0.004023 +0.915000 0.004205 +0.920000 0.004387 +0.925000 0.004504 +0.930000 0.004620 +0.935000 0.004661 +0.940000 0.004702 +0.945000 0.004658 +0.950000 0.004614 +0.955000 0.004476 +0.960000 0.004338 +0.965000 0.004084 +0.970000 0.003829 +0.975000 0.003436 +0.980000 0.003042 +0.990000 0.001910 +1.000000 0.000000 diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_AeroDyn_blade.dat b/examples/NREL_5MW_Monopile/NREL_5MW_AeroDyn_blade.dat new file mode 100644 index 0000000..afef347 --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_AeroDyn_blade.dat @@ -0,0 +1,28 @@ +------- AERODYN v15.00.* BLADE DEFINITION INPUT FILE ------------------------------------- +NREL 5.0 MW offshore baseline aerodynamic blade input properties; note that we need to add the aerodynamic center to this file +====== Blade Properties ================================================================= + 19 NumBlNds - Number of blade nodes used in the analysis (-) + BlSpn BlCrvAC BlSwpAC BlCrvAng BlTwist BlChord BlAFID BlCb BlCenBn BlCenBt + (m) (m) (m) (deg) (deg) (m) (-) (-) (m) (m) +0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 1.3308000E+01 3.5420000E+00 1 0.0 0.0 0.0 +1.3667000E+00 -8.1531745E-04 -3.4468858E-03 0.0000000E+00 1.3308000E+01 3.5420000E+00 1 0.0 0.0 0.0 +4.1000000E+00 -2.4839790E-02 -1.0501421E-01 0.0000000E+00 1.3308000E+01 3.8540000E+00 1 0.0 0.0 0.0 +6.8333000E+00 -5.9469375E-02 -2.5141635E-01 0.0000000E+00 1.3308000E+01 4.1670000E+00 2 0.0 0.0 0.0 +1.0250000E+01 -1.0909141E-01 -4.6120149E-01 0.0000000E+00 1.3308000E+01 4.5570000E+00 3 0.0 0.0 0.0 +1.4350000E+01 -1.1573354E-01 -5.6986665E-01 0.0000000E+00 1.1480000E+01 4.6520000E+00 4 0.0 0.0 0.0 +1.8450000E+01 -9.8316709E-02 -5.4850833E-01 0.0000000E+00 1.0162000E+01 4.4580000E+00 4 0.0 0.0 0.0 +2.2550000E+01 -8.3186967E-02 -5.2457001E-01 0.0000000E+00 9.0110000E+00 4.2490000E+00 5 0.0 0.0 0.0 +2.6650000E+01 -6.7933232E-02 -4.9624675E-01 0.0000000E+00 7.7950000E+00 4.0070000E+00 6 0.0 0.0 0.0 +3.0750000E+01 -5.3393159E-02 -4.6544755E-01 0.0000000E+00 6.5440000E+00 3.7480000E+00 6 0.0 0.0 0.0 +3.4850000E+01 -4.0899260E-02 -4.3583519E-01 0.0000000E+00 5.3610000E+00 3.5020000E+00 7 0.0 0.0 0.0 +3.8950000E+01 -2.9722933E-02 -4.0591323E-01 0.0000000E+00 4.1880000E+00 3.2560000E+00 7 0.0 0.0 0.0 +4.3050000E+01 -2.0511081E-02 -3.7569051E-01 0.0000000E+00 3.1250000E+00 3.0100000E+00 8 0.0 0.0 0.0 +4.7150000E+01 -1.3980013E-02 -3.4521705E-01 0.0000000E+00 2.3190000E+00 2.7640000E+00 8 0.0 0.0 0.0 +5.1250000E+01 -8.3819737E-03 -3.1463837E-01 0.0000000E+00 1.5260000E+00 2.5180000E+00 8 0.0 0.0 0.0 +5.4666700E+01 -4.3546914E-03 -2.8909220E-01 0.0000000E+00 8.6300000E-01 2.3130000E+00 8 0.0 0.0 0.0 +5.7400000E+01 -1.6838383E-03 -2.6074456E-01 0.0000000E+00 3.7000000E-01 2.0860000E+00 8 0.0 0.0 0.0 +6.0133300E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 0.0 0.0 0.0 +6.1499900E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 0.0 0.0 0.0 + +!bjj: because of precision in the BD-AD coupling, 61.5m didn't work, so I changed it to 61.4999m +6.1500000E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 0.0 0.0 0.0 diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_ElastoDyn_Blade.dat b/examples/NREL_5MW_Monopile/NREL_5MW_ElastoDyn_Blade.dat new file mode 100644 index 0000000..4ceba92 --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_ElastoDyn_Blade.dat @@ -0,0 +1,83 @@ +------- ELASTODYN V1.00.* INDIVIDUAL BLADE INPUT FILE -------------------------- +NREL 5.0 MW offshore baseline blade input properties. +---------------------- BLADE PARAMETERS ---------------------------------------- + 49 NBlInpSt - Number of blade input stations (-) + 0.477465 BldFlDmp(1) - Blade flap mode #1 structural damping in percent of critical (%) + 0.477465 BldFlDmp(2) - Blade flap mode #2 structural damping in percent of critical (%) + 0.477465 BldEdDmp(1) - Blade edge mode #1 structural damping in percent of critical (%) +---------------------- BLADE ADJUSTMENT FACTORS -------------------------------- + 1 FlStTunr(1) - Blade flapwise modal stiffness tuner, 1st mode (-) + 1 FlStTunr(2) - Blade flapwise modal stiffness tuner, 2nd mode (-) + 1.04536 AdjBlMs - Factor to adjust blade mass density (-) !bjj: value for AD14=1.04536; value for AD15=1.057344 (it would be nice to enter the requested blade mass instead of a factor here) + 1 AdjFlSt - Factor to adjust blade flap stiffness (-) + 1 AdjEdSt - Factor to adjust blade edge stiffness (-) +---------------------- DISTRIBUTED BLADE PROPERTIES ---------------------------- + BlFract PitchAxis StrcTwst BMassDen FlpStff EdgStff + (-) (-) (deg) (kg/m) (Nm^2) (Nm^2) +0.0000000E+00 2.5000000E-01 1.3308000E+01 6.7893500E+02 1.8110000E+10 1.8113600E+10 +3.2500000E-03 2.5000000E-01 1.3308000E+01 6.7893500E+02 1.8110000E+10 1.8113600E+10 +1.9510000E-02 2.5049000E-01 1.3308000E+01 7.7336300E+02 1.9424900E+10 1.9558600E+10 +3.5770000E-02 2.5490000E-01 1.3308000E+01 7.4055000E+02 1.7455900E+10 1.9497800E+10 +5.2030000E-02 2.6716000E-01 1.3308000E+01 7.4004200E+02 1.5287400E+10 1.9788800E+10 +6.8290000E-02 2.7941000E-01 1.3308000E+01 5.9249600E+02 1.0782400E+10 1.4858500E+10 +8.4550000E-02 2.9167000E-01 1.3308000E+01 4.5027500E+02 7.2297200E+09 1.0220600E+10 +1.0081000E-01 3.0392000E-01 1.3308000E+01 4.2405400E+02 6.3095400E+09 9.1447000E+09 +1.1707000E-01 3.1618000E-01 1.3308000E+01 4.0063800E+02 5.5283600E+09 8.0631600E+09 +1.3335000E-01 3.2844000E-01 1.3308000E+01 3.8206200E+02 4.9800600E+09 6.8844400E+09 +1.4959000E-01 3.4069000E-01 1.3308000E+01 3.9965500E+02 4.9368400E+09 7.0091800E+09 +1.6585000E-01 3.5294000E-01 1.3308000E+01 4.2632100E+02 4.6916600E+09 7.1676800E+09 +1.8211000E-01 3.6519000E-01 1.3181000E+01 4.1682000E+02 3.9494600E+09 7.2716600E+09 +1.9837000E-01 3.7500000E-01 1.2848000E+01 4.0618600E+02 3.3865200E+09 7.0817000E+09 +2.1465000E-01 3.7500000E-01 1.2192000E+01 3.8142000E+02 2.9337400E+09 6.2445300E+09 +2.3089000E-01 3.7500000E-01 1.1561000E+01 3.5282200E+02 2.5689600E+09 5.0489600E+09 +2.4715000E-01 3.7500000E-01 1.1072000E+01 3.4947700E+02 2.3886500E+09 4.9484900E+09 +2.6341000E-01 3.7500000E-01 1.0792000E+01 3.4653800E+02 2.2719900E+09 4.8080200E+09 +2.9595000E-01 3.7500000E-01 1.0232000E+01 3.3933300E+02 2.0500500E+09 4.5014000E+09 +3.2846000E-01 3.7500000E-01 9.6720000E+00 3.3000400E+02 1.8282500E+09 4.2440700E+09 +3.6098000E-01 3.7500000E-01 9.1100000E+00 3.2199000E+02 1.5887100E+09 3.9952800E+09 +3.9350000E-01 3.7500000E-01 8.5340000E+00 3.1382000E+02 1.3619300E+09 3.7507600E+09 +4.2602000E-01 3.7500000E-01 7.9320000E+00 2.9473400E+02 1.1023800E+09 3.4471400E+09 +4.5855000E-01 3.7500000E-01 7.3210000E+00 2.8712000E+02 8.7580000E+08 3.1390700E+09 +4.9106000E-01 3.7500000E-01 6.7110000E+00 2.6334300E+02 6.8130000E+08 2.7342400E+09 +5.2358000E-01 3.7500000E-01 6.1220000E+00 2.5320700E+02 5.3472000E+08 2.5548700E+09 +5.5610000E-01 3.7500000E-01 5.5460000E+00 2.4166600E+02 4.0890000E+08 2.3340300E+09 +5.8862000E-01 3.7500000E-01 4.9710000E+00 2.2063800E+02 3.1454000E+08 1.8287300E+09 +6.2115000E-01 3.7500000E-01 4.4010000E+00 2.0029300E+02 2.3863000E+08 1.5841000E+09 +6.5366000E-01 3.7500000E-01 3.8340000E+00 1.7940400E+02 1.7588000E+08 1.3233600E+09 +6.8618000E-01 3.7500000E-01 3.3320000E+00 1.6509400E+02 1.2601000E+08 1.1836800E+09 +7.1870000E-01 3.7500000E-01 2.8900000E+00 1.5441100E+02 1.0726000E+08 1.0201600E+09 +7.5122000E-01 3.7500000E-01 2.5030000E+00 1.3893500E+02 9.0880000E+07 7.9781000E+08 +7.8376000E-01 3.7500000E-01 2.1160000E+00 1.2955500E+02 7.6310000E+07 7.0961000E+08 +8.1626000E-01 3.7500000E-01 1.7300000E+00 1.0726400E+02 6.1050000E+07 5.1819000E+08 +8.4878000E-01 3.7500000E-01 1.3420000E+00 9.8776000E+01 4.9480000E+07 4.5487000E+08 +8.8130000E-01 3.7500000E-01 9.5400000E-01 9.0248000E+01 3.9360000E+07 3.9512000E+08 +8.9756000E-01 3.7500000E-01 7.6000000E-01 8.3001000E+01 3.4670000E+07 3.5372000E+08 +9.1382000E-01 3.7500000E-01 5.7400000E-01 7.2906000E+01 3.0410000E+07 3.0473000E+08 +9.3008000E-01 3.7500000E-01 4.0400000E-01 6.8772000E+01 2.6520000E+07 2.8142000E+08 +9.3821000E-01 3.7500000E-01 3.1900000E-01 6.6264000E+01 2.3840000E+07 2.6171000E+08 +9.4636000E-01 3.7500000E-01 2.5300000E-01 5.9340000E+01 1.9630000E+07 1.5881000E+08 +9.5447000E-01 3.7500000E-01 2.1600000E-01 5.5914000E+01 1.6000000E+07 1.3788000E+08 +9.6260000E-01 3.7500000E-01 1.7800000E-01 5.2484000E+01 1.2830000E+07 1.1879000E+08 +9.7073000E-01 3.7500000E-01 1.4000000E-01 4.9114000E+01 1.0080000E+07 1.0163000E+08 +9.7886000E-01 3.7500000E-01 1.0100000E-01 4.5818000E+01 7.5500000E+06 8.5070000E+07 +9.8699000E-01 3.7500000E-01 6.2000000E-02 4.1669000E+01 4.6000000E+06 6.4260000E+07 +9.9512000E-01 3.7500000E-01 2.3000000E-02 1.1453000E+01 2.5000000E+05 6.6100000E+06 +1.0000000E+00 3.7500000E-01 0.0000000E+00 1.0319000E+01 1.7000000E+05 5.0100000E+06 +---------------------- BLADE MODE SHAPES --------------------------------------- + 0.0622 BldFl1Sh(2) - Flap mode 1, coeff of x^2 + 1.7254 BldFl1Sh(3) - , coeff of x^3 + -3.2452 BldFl1Sh(4) - , coeff of x^4 + 4.7131 BldFl1Sh(5) - , coeff of x^5 + -2.2555 BldFl1Sh(6) - , coeff of x^6 + -0.5809 BldFl2Sh(2) - Flap mode 2, coeff of x^2 + 1.2067 BldFl2Sh(3) - , coeff of x^3 + -15.5349 BldFl2Sh(4) - , coeff of x^4 + 29.7347 BldFl2Sh(5) - , coeff of x^5 + -13.8255 BldFl2Sh(6) - , coeff of x^6 + 0.3627 BldEdgSh(2) - Edge mode 1, coeff of x^2 + 2.5337 BldEdgSh(3) - , coeff of x^3 + -3.5772 BldEdgSh(4) - , coeff of x^4 + 2.376 BldEdgSh(5) - , coeff of x^5 + -0.6952 BldEdgSh(6) - , coeff of x^6 + + diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_InflowWind.dat b/examples/NREL_5MW_Monopile/NREL_5MW_InflowWind.dat new file mode 100644 index 0000000..bbe476c --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_InflowWind.dat @@ -0,0 +1,71 @@ +------- InflowWind v3.01.* INPUT FILE ------------------------------------------------------------------------- +13 m/s Steady Wind +--------------------------------------------------------------------------------------------------------------- + False Echo - Echo input data to .ech (flag) + 1 WindType - switch for wind file type (1=steady; 2=uniform; 3=binary TurbSim FF; 4=binary Bladed-style FF; 5=HAWC format; 6=User defined; 7=native Bladed FF) + 0 PropagationDir - Direction of wind propagation (meteorological rotation from aligned with X (positive rotates towards -Y) -- degrees) (not used for native Bladed format WindType=7) + 0 VFlowAng - Upflow angle (degrees) (not used for native Bladed format WindType=7) + False VelInterpCubic - Use cubic interpolation for velocity in time (false=linear, true=cubic) [Used with WindType=2,3,4,5,7] + 1 NWindVel - Number of points to output the wind velocity (0 to 9) + 0 WindVxiList - List of coordinates in the inertial X direction (m) + 0 WindVyiList - List of coordinates in the inertial Y direction (m) + 90 WindVziList - List of coordinates in the inertial Z direction (m) +================== Parameters for Steady Wind Conditions [used only for WindType = 1] ========================= + 13 HWindSpeed - Horizontal wind speed (m/s) + 90 RefHt - Reference height for horizontal wind speed (m) + 0.2 PLExp - Power law exponent (-) +================== Parameters for Uniform wind file [used only for WindType = 2] ============================ +"unused" Filename_Uni - Filename of time series data for uniform wind field. (-) + 90 RefHt_Uni - Reference height for horizontal wind speed (m) + 125.88 RefLength - Reference length for linear horizontal and vertical sheer (-) +================== Parameters for Binary TurbSim Full-Field files [used only for WindType = 3] ============== +"unused" FileName_BTS - Name of the Full field wind file to use (.bts) +================== Parameters for Binary Bladed-style Full-Field files [used only for WindType = 4 or WindType = 7] ========= +"unused" FileNameRoot - WindType=4: Rootname of the full-field wind file to use (.wnd, .sum); WindType=7: name of the intermediate file with wind scaling values +False TowerFile - Have tower file (.twr) (flag) ignored when WindType = 7 +================== Parameters for HAWC-format binary files [Only used with WindType = 5] ===================== +"unused" FileName_u - name of the file containing the u-component fluctuating wind (.bin) +"unused" FileName_v - name of the file containing the v-component fluctuating wind (.bin) +"unused" FileName_w - name of the file containing the w-component fluctuating wind (.bin) + 64 nx - number of grids in the x direction (in the 3 files above) (-) + 32 ny - number of grids in the y direction (in the 3 files above) (-) + 32 nz - number of grids in the z direction (in the 3 files above) (-) + 16 dx - distance (in meters) between points in the x direction (m) + 3 dy - distance (in meters) between points in the y direction (m) + 3 dz - distance (in meters) between points in the z direction (m) + 90 RefHt_Hawc - reference height; the height (in meters) of the vertical center of the grid (m) + ------------- Scaling parameters for turbulence --------------------------------------------------------- + 1 ScaleMethod - Turbulence scaling method [0 = none, 1 = direct scaling, 2 = calculate scaling factor based on a desired standard deviation] + 1 SFx - Turbulence scaling factor for the x direction (-) [ScaleMethod=1] + 1 SFy - Turbulence scaling factor for the y direction (-) [ScaleMethod=1] + 1 SFz - Turbulence scaling factor for the z direction (-) [ScaleMethod=1] + 12 SigmaFx - Turbulence standard deviation to calculate scaling from in x direction (m/s) [ScaleMethod=2] + 8 SigmaFy - Turbulence standard deviation to calculate scaling from in y direction (m/s) [ScaleMethod=2] + 2 SigmaFz - Turbulence standard deviation to calculate scaling from in z direction (m/s) [ScaleMethod=2] + ------------- Mean wind profile parameters (added to HAWC-format files) --------------------------------- + 5 URef - Mean u-component wind speed at the reference height (m/s) + 2 WindProfile - Wind profile type (0=constant;1=logarithmic,2=power law) + 0 PLExp_Hawc - Power law exponent (-) (used for PL wind profile type only) + 0.03 Z0 - Surface roughness length (m) (used for LG wind profile type only) + 0 XOffset - Initial offset in +x direction (shift of wind box) +================== LIDAR Parameters =========================================================================== + 0 SensorType - Switch for lidar configuration (0 = None, 1 = Single Point Beam(s), 2 = Continuous, 3 = Pulsed) + 0 NumPulseGate - Number of lidar measurement gates (used when SensorType = 3) + 30 PulseSpacing - Distance between range gates (m) (used when SensorType = 3) + 0 NumBeam - Number of lidar measurement beams (0-5)(used when SensorType = 1) + -200 FocalDistanceX - Focal distance co-ordinates of the lidar beam in the x direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) + 0 FocalDistanceY - Focal distance co-ordinates of the lidar beam in the y direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) + 0 FocalDistanceZ - Focal distance co-ordinates of the lidar beam in the z direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) +0.0 0.0 0.0 RotorApexOffsetPos - Offset of the lidar from hub height (m) + 17 URefLid - Reference average wind speed for the lidar[m/s] + 0.25 MeasurementInterval - Time between each measurement [s] + False LidRadialVel - TRUE => return radial component, FALSE => return 'x' direction estimate + 1 ConsiderHubMotion - Flag whether to consider the hub motion's impact on Lidar measurements +====================== OUTPUT ================================================== +False SumPrint - Print summary data to .IfW.sum (flag) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +"Wind1VelX" X-direction wind velocity at point WindList(1) +"Wind1VelY" Y-direction wind velocity at point WindList(1) +"Wind1VelZ" Z-direction wind velocity at point WindList(1) +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +--------------------------------------------------------------------------------------- diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_Monopile.fst b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile.fst new file mode 100644 index 0000000..17c6c15 --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile.fst @@ -0,0 +1,71 @@ +------- OpenFAST EXAMPLE INPUT FILE ------------------------------------------- +FAST Certification Test #21: NREL 5.0 MW Baseline Offshore Turbine with Monopile Jacket Configuration +---------------------- SIMULATION CONTROL -------------------------------------- +True Echo - Echo input data to .ech (flag) +"FATAL" AbortLevel - Error level when simulation should abort (string) {"WARNING", "SEVERE", "FATAL"} + 60 TMax - Total run time (s) + 0.01 DT - Recommended module time step (s) + 2 InterpOrder - Interpolation order for input/output time history (-) {1=linear, 2=quadratic} + 1 NumCrctn - Number of correction iterations (-) {0=explicit calculation, i.e., no corrections} + 99999 DT_UJac - Time between calls to get Jacobians (s) + 1E+06 UJacSclFact - Scaling factor used in Jacobians (-) +---------------------- FEATURE SWITCHES AND FLAGS ------------------------------ + 1 CompElast - Compute structural dynamics (switch) {1=ElastoDyn; 2=ElastoDyn + BeamDyn for blades} + 1 CompInflow - Compute inflow wind velocities (switch) {0=still air; 1=InflowWind; 2=external from OpenFOAM} + 2 CompAero - Compute aerodynamic loads (switch) {0=None; 1=AeroDyn v14; 2=AeroDyn v15} + 1 CompServo - Compute control and electrical-drive dynamics (switch) {0=None; 1=ServoDyn} + 1 CompHydro - Compute hydrodynamic loads (switch) {0=None; 1=HydroDyn} + 1 CompSub - Compute sub-structural dynamics (switch) {0=None; 1=SubDyn; 2=External Platform MCKF} + 0 CompMooring - Compute mooring system (switch) {0=None; 1=MAP++; 2=FEAMooring; 3=MoorDyn; 4=OrcaFlex} + 0 CompIce - Compute ice loads (switch) {0=None; 1=IceFloe; 2=IceDyn} + 0 MHK - MHK turbine type (switch) {0=Not an MHK turbine; 1=Fixed MHK turbine; 2=Floating MHK turbine} +---------------------- ENVIRONMENTAL CONDITIONS -------------------------------- + 9.80665 Gravity - Gravitational acceleration (m/s^2) + 1.225 AirDens - Air density (kg/m^3) + 1025 WtrDens - Water density (kg/m^3) + 1.464E-05 KinVisc - Kinematic viscosity of working fluid (m^2/s) + 335 SpdSound - Speed of sound in working fluid (m/s) + 103500 Patm - Atmospheric pressure (Pa) [used only for an MHK turbine cavitation check] + 1700 Pvap - Vapour pressure of working fluid (Pa) [used only for an MHK turbine cavitation check] + 50 WtrDpth - Water depth (m) + 0 MSL2SWL - Offset between still-water level and mean sea level (m) [positive upward] +---------------------- INPUT FILES --------------------------------------------- +"NREL_5MW_Monopile_ElastoDyn.dat" EDFile - Name of file containing ElastoDyn input parameters (quoted string) +"NREL_5MW_BeamDyn.dat" BDBldFile(1) - Name of file containing BeamDyn input parameters for blade 1 (quoted string) +"NREL_5MW_BeamDyn.dat" BDBldFile(2) - Name of file containing BeamDyn input parameters for blade 2 (quoted string) +"NREL_5MW_BeamDyn.dat" BDBldFile(3) - Name of file containing BeamDyn input parameters for blade 3 (quoted string) +"NREL_5MW_InflowWind.dat" InflowFile - Name of file containing inflow wind input parameters (quoted string) +"NREL_5MW_Monopile_AeroDyn15.dat" AeroFile - Name of file containing aerodynamic input parameters (quoted string) +"NREL_5MW_Monopile_ServoDyn.dat" ServoFile - Name of file containing control and electrical-drive input parameters (quoted string) +"NREL_5MW_Monopile_HydroDyn.dat" HydroFile - Name of file containing hydrodynamic input parameters (quoted string) +"NREL_5MW_Monopile_SubDyn.dat" SubFile - Name of file containing sub-structural input parameters (quoted string) +"unused" MooringFile - Name of file containing mooring system input parameters (quoted string) +"unused" IceFile - Name of file containing ice input parameters (quoted string) +---------------------- OUTPUT -------------------------------------------------- +True SumPrint - Print summary data to ".sum" (flag) + 1 SttsTime - Amount of time between screen status messages (s) + 99999 ChkptTime - Amount of time between creating checkpoint files for potential restart (s) + 0.05 DT_Out - Time step for tabular output (s) (or "default") + 0 TStart - Time to begin tabular output (s) + 0 OutFileFmt - Format for tabular (time-marching) output file (switch) {0: uncompressed binary [.outb], 1: text file [.out], 2: binary file [.outb], 3: both 1 and 2} +True TabDelim - Use tab delimiters in text tabular output file? (flag) {uses spaces if false} +"ES10.3E2" OutFmt - Format used for text tabular output, excluding the time channel. Resulting field should be 10 characters. (quoted string) +---------------------- LINEARIZATION ------------------------------------------- +False Linearize - Linearization analysis (flag) +False CalcSteady - Calculate a steady-state periodic operating point before linearization? [unused if Linearize=False] (flag) + 3 TrimCase - Controller parameter to be trimmed {1:yaw; 2:torque; 3:pitch} [used only if CalcSteady=True] (-) + 0.001 TrimTol - Tolerance for the rotational speed convergence [used only if CalcSteady=True] (-) + 0.01 TrimGain - Proportional gain for the rotational speed error (>0) [used only if CalcSteady=True] (rad/(rad/s) for yaw or pitch; Nm/(rad/s) for torque) + 0 Twr_Kdmp - Damping factor for the tower [used only if CalcSteady=True] (N/(m/s)) + 0 Bld_Kdmp - Damping factor for the blades [used only if CalcSteady=True] (N/(m/s)) + 2 NLinTimes - Number of times to linearize (-) [>=1] [unused if Linearize=False] + 30, 60 LinTimes - List of times at which to linearize (s) [1 to NLinTimes] [used only when Linearize=True and CalcSteady=False] + 1 LinInputs - Inputs included in linearization (switch) {0=none; 1=standard; 2=all module inputs (debug)} [unused if Linearize=False] + 1 LinOutputs - Outputs included in linearization (switch) {0=none; 1=from OutList(s); 2=all module outputs (debug)} [unused if Linearize=False] +False LinOutJac - Include full Jacobians in linearization output (for debug) (flag) [unused if Linearize=False; used only if LinInputs=LinOutputs=2] +False LinOutMod - Write module-level linearization output files in addition to output for full system? (flag) [unused if Linearize=False] +---------------------- VISUALIZATION ------------------------------------------ + 0 WrVTK - VTK visualization data output: (switch) {0=none; 1=initialization data only; 2=animation; 3=mode shapes} + 2 VTK_type - Type of VTK visualization data: (switch) {1=surfaces; 2=basic meshes (lines/points); 3=all meshes (debug)} [unused if WrVTK=0] +false VTK_fields - Write mesh fields to VTK data files? (flag) {true/false} [unused if WrVTK=0] + 15 VTK_fps - Frame rate for VTK output (frames per second){will use closest integer multiple of DT} [used only if WrVTK=2 or WrVTK=3] diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_Monopile.json b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile.json new file mode 100755 index 0000000..c82ed44 --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile.json @@ -0,0 +1,6556 @@ +{ + "Info": { + "Date": "Monday, 13-May-24 11:49:33 EDT", + "Path": "/Users/dslaught/projects/acdc/acdc-app/examples/NREL_5MW_Monopile/NREL_5MW_Monopile.json" + }, + "Model": { + "HasAero": true, + "ImportedPaths": [ + "Airfoils/Cylinder1.dat", + "Airfoils/Cylinder2.dat", + "Airfoils/DU21_A17.dat", + "Airfoils/DU25_A17.dat", + "Airfoils/DU30_A17.dat", + "Airfoils/DU35_A17.dat", + "Airfoils/DU40_A17.dat", + "Airfoils/NACA64_A17.dat", + "NREL_5MW_AeroDyn_blade.dat", + "NREL_5MW_ElastoDyn_Blade.dat", + "NREL_5MW_InflowWind.dat", + "NREL_5MW_Monopile.fst", + "NREL_5MW_Monopile_AeroDyn15.dat", + "NREL_5MW_Monopile_ElastoDyn.dat", + "NREL_5MW_Monopile_ElastoDyn_Tower.dat", + "NREL_5MW_Monopile_HydroDyn.dat", + "NREL_5MW_Monopile_ServoDyn.dat", + "NREL_5MW_Monopile_SubDyn.dat" + ], + "Files": { + "Main": [ + { + "Name": "NREL_5MW_Monopile.fst", + "Type": "Main", + "Lines": [ + "------- OpenFAST EXAMPLE INPUT FILE -------------------------------------------", + "FAST Certification Test #21: NREL 5.0 MW Baseline Offshore Turbine with Monopile Jacket Configuration", + "---------------------- SIMULATION CONTROL --------------------------------------", + "True Echo - Echo input data to \u003cRootName\u003e.ech (flag)", + "\"FATAL\" AbortLevel - Error level when simulation should abort (string) {\"WARNING\", \"SEVERE\", \"FATAL\"}", + " 60 TMax - Total run time (s)", + " 0.01 DT - Recommended module time step (s)", + " 2 InterpOrder - Interpolation order for input/output time history (-) {1=linear, 2=quadratic}", + " 1 NumCrctn - Number of correction iterations (-) {0=explicit calculation, i.e., no corrections}", + " 99999 DT_UJac - Time between calls to get Jacobians (s)", + " 1E+06 UJacSclFact - Scaling factor used in Jacobians (-)", + "---------------------- FEATURE SWITCHES AND FLAGS ------------------------------", + " 1 CompElast - Compute structural dynamics (switch) {1=ElastoDyn; 2=ElastoDyn + BeamDyn for blades}", + " 1 CompInflow - Compute inflow wind velocities (switch) {0=still air; 1=InflowWind; 2=external from OpenFOAM}", + " 2 CompAero - Compute aerodynamic loads (switch) {0=None; 1=AeroDyn v14; 2=AeroDyn v15}", + " 1 CompServo - Compute control and electrical-drive dynamics (switch) {0=None; 1=ServoDyn}", + " 1 CompHydro - Compute hydrodynamic loads (switch) {0=None; 1=HydroDyn}", + " 1 CompSub - Compute sub-structural dynamics (switch) {0=None; 1=SubDyn; 2=External Platform MCKF}", + " 0 CompMooring - Compute mooring system (switch) {0=None; 1=MAP++; 2=FEAMooring; 3=MoorDyn; 4=OrcaFlex}", + " 0 CompIce - Compute ice loads (switch) {0=None; 1=IceFloe; 2=IceDyn}", + " 0 MHK - MHK turbine type (switch) {0=Not an MHK turbine; 1=Fixed MHK turbine; 2=Floating MHK turbine}", + "---------------------- ENVIRONMENTAL CONDITIONS --------------------------------", + " 9.80665 Gravity - Gravitational acceleration (m/s^2)", + " 1.225 AirDens - Air density (kg/m^3)", + " 1025 WtrDens - Water density (kg/m^3)", + " 1.464E-05 KinVisc - Kinematic viscosity of working fluid (m^2/s)", + " 335 SpdSound - Speed of sound in working fluid (m/s)", + " 103500 Patm - Atmospheric pressure (Pa) [used only for an MHK turbine cavitation check]", + " 1700 Pvap - Vapour pressure of working fluid (Pa) [used only for an MHK turbine cavitation check]", + " 50 WtrDpth - Water depth (m)", + " 0 MSL2SWL - Offset between still-water level and mean sea level (m) [positive upward]", + "---------------------- INPUT FILES ---------------------------------------------", + "\"NREL_5MW_Monopile_ElastoDyn.dat\" EDFile - Name of file containing ElastoDyn input parameters (quoted string)", + "\"NREL_5MW_BeamDyn.dat\" BDBldFile(1) - Name of file containing BeamDyn input parameters for blade 1 (quoted string)", + "\"NREL_5MW_BeamDyn.dat\" BDBldFile(2) - Name of file containing BeamDyn input parameters for blade 2 (quoted string)", + "\"NREL_5MW_BeamDyn.dat\" BDBldFile(3) - Name of file containing BeamDyn input parameters for blade 3 (quoted string)", + "\"NREL_5MW_InflowWind.dat\" InflowFile - Name of file containing inflow wind input parameters (quoted string)", + "\"NREL_5MW_Monopile_AeroDyn15.dat\" AeroFile - Name of file containing aerodynamic input parameters (quoted string)", + "\"NREL_5MW_Monopile_ServoDyn.dat\" ServoFile - Name of file containing control and electrical-drive input parameters (quoted string)", + "\"NREL_5MW_Monopile_HydroDyn.dat\" HydroFile - Name of file containing hydrodynamic input parameters (quoted string)", + "\"NREL_5MW_Monopile_SubDyn.dat\" SubFile - Name of file containing sub-structural input parameters (quoted string)", + "\"unused\" MooringFile - Name of file containing mooring system input parameters (quoted string)", + "\"unused\" IceFile - Name of file containing ice input parameters (quoted string)", + "---------------------- OUTPUT --------------------------------------------------", + "True SumPrint - Print summary data to \"\u003cRootName\u003e.sum\" (flag)", + " 1 SttsTime - Amount of time between screen status messages (s)", + " 99999 ChkptTime - Amount of time between creating checkpoint files for potential restart (s)", + " 0.05 DT_Out - Time step for tabular output (s) (or \"default\")", + " 0 TStart - Time to begin tabular output (s)", + " 0 OutFileFmt - Format for tabular (time-marching) output file (switch) {0: uncompressed binary [\u003cRootName\u003e.outb], 1: text file [\u003cRootName\u003e.out], 2: binary file [\u003cRootName\u003e.outb], 3: both 1 and 2}", + "True TabDelim - Use tab delimiters in text tabular output file? (flag) {uses spaces if false}", + "\"ES10.3E2\" OutFmt - Format used for text tabular output, excluding the time channel. Resulting field should be 10 characters. (quoted string)", + "---------------------- LINEARIZATION -------------------------------------------", + "False Linearize - Linearization analysis (flag)", + "False CalcSteady - Calculate a steady-state periodic operating point before linearization? [unused if Linearize=False] (flag)", + " 3 TrimCase - Controller parameter to be trimmed {1:yaw; 2:torque; 3:pitch} [used only if CalcSteady=True] (-)", + " 0.001 TrimTol - Tolerance for the rotational speed convergence [used only if CalcSteady=True] (-)", + " 0.01 TrimGain - Proportional gain for the rotational speed error (\u003e0) [used only if CalcSteady=True] (rad/(rad/s) for yaw or pitch; Nm/(rad/s) for torque)", + " 0 Twr_Kdmp - Damping factor for the tower [used only if CalcSteady=True] (N/(m/s))", + " 0 Bld_Kdmp - Damping factor for the blades [used only if CalcSteady=True] (N/(m/s))", + " 2 NLinTimes - Number of times to linearize (-) [\u003e=1] [unused if Linearize=False]", + " 30, 60 LinTimes - List of times at which to linearize (s) [1 to NLinTimes] [used only when Linearize=True and CalcSteady=False]", + " 1 LinInputs - Inputs included in linearization (switch) {0=none; 1=standard; 2=all module inputs (debug)} [unused if Linearize=False]", + " 1 LinOutputs - Outputs included in linearization (switch) {0=none; 1=from OutList(s); 2=all module outputs (debug)} [unused if Linearize=False]", + "False LinOutJac - Include full Jacobians in linearization output (for debug) (flag) [unused if Linearize=False; used only if LinInputs=LinOutputs=2]", + "False LinOutMod - Write module-level linearization output files in addition to output for full system? (flag) [unused if Linearize=False]", + "---------------------- VISUALIZATION ------------------------------------------", + " 0 WrVTK - VTK visualization data output: (switch) {0=none; 1=initialization data only; 2=animation; 3=mode shapes}", + " 2 VTK_type - Type of VTK visualization data: (switch) {1=surfaces; 2=basic meshes (lines/points); 3=all meshes (debug)} [unused if WrVTK=0]", + "false VTK_fields - Write mesh fields to VTK data files? (flag) {true/false} [unused if WrVTK=0]", + " 15 VTK_fps - Frame rate for VTK output (frames per second){will use closest integer multiple of DT} [used only if WrVTK=2 or WrVTK=3]" + ], + "TMax": { + "Name": "TMax", + "Type": "Real", + "Desc": "Total run time (s)", + "Line": 6, + "Value": 5 + }, + "DT": { + "Name": "DT", + "Type": "Real", + "Desc": "Recommended module time step (s)", + "Line": 7, + "Value": 0.005 + }, + "CompElast": { + "Name": "CompElast", + "Type": "Integer", + "Desc": "Compute structural dynamics (switch) {1=ElastoDyn; 2=ElastoDyn + BeamDyn for blades}", + "Line": 13, + "Value": 1, + "Size": false + }, + "CompInflow": { + "Name": "CompInflow", + "Type": "Integer", + "Desc": "Compute inflow wind velocities (switch) {0=still air; 1=InflowWind; 2=external from OpenFOAM}", + "Line": 14, + "Value": 1, + "Size": false + }, + "CompAero": { + "Name": "CompAero", + "Type": "Integer", + "Desc": "Compute aerodynamic loads (switch) {0=None; 1=AeroDyn v14; 2=AeroDyn v15}", + "Line": 15, + "Value": 2, + "Size": false + }, + "CompServo": { + "Name": "CompServo", + "Type": "Integer", + "Desc": "Compute control and electrical-drive dynamics (switch) {0=None; 1=ServoDyn}", + "Line": 16, + "Value": 1, + "Size": false + }, + "CompHydro": { + "Name": "CompHydro", + "Type": "Integer", + "Desc": "Compute hydrodynamic loads (switch) {0=None; 1=HydroDyn}", + "Line": 17, + "Value": 1, + "Size": false + }, + "CompSub": { + "Name": "CompSub", + "Type": "Integer", + "Desc": "Compute sub-structural dynamics (switch) {0=None; 1=SubDyn; 2=External Platform MCKF}", + "Line": 18, + "Value": 1, + "Size": false + }, + "CompMooring": { + "Name": "CompMooring", + "Type": "Integer", + "Desc": "Compute mooring system (switch) {0=None; 1=MAP++; 2=FEAMooring; 3=MoorDyn; 4=OrcaFlex}", + "Line": 19, + "Value": 0, + "Size": false + }, + "CompIce": { + "Name": "CompIce", + "Type": "Integer", + "Desc": "Compute ice loads (switch) {0=None; 1=IceFloe; 2=IceDyn}", + "Line": 20, + "Value": 0, + "Size": false + }, + "MHK": { + "Name": "MHK", + "Type": "Integer", + "Desc": "MHK turbine type (switch) {0=Not an MHK turbine; 1=Fixed MHK turbine; 2=Floating MHK turbine}", + "Line": 21, + "Value": 0, + "Size": false + }, + "Gravity": { + "Name": "Gravity", + "Type": "Real", + "Desc": "Gravitational acceleration (m/s^2)", + "Line": 23, + "Value": 9.80665 + }, + "EDFile": { + "Name": "EDFile", + "Type": "Path", + "Desc": "Name of file containing ElastoDyn input parameters (quoted string)", + "Line": 33, + "Value": "NREL_5MW_Monopile_ElastoDyn.dat", + "FileType": "ElastoDyn", + "Root": false + }, + "BDBldFile1": { + "Name": "BDBldFile(1)", + "Type": "Path", + "Desc": "Name of file containing BeamDyn input parameters for blade 1 (quoted string)", + "Line": 34, + "Value": "FileNotFound", + "FileType": "BeamDyn", + "Root": false + }, + "BDBldFile2": { + "Name": "BDBldFile(2)", + "Type": "Path", + "Desc": "Name of file containing BeamDyn input parameters for blade 2 (quoted string)", + "Line": 35, + "Value": "FileNotFound", + "FileType": "BeamDyn", + "Root": false + }, + "BDBldFile3": { + "Name": "BDBldFile(3)", + "Type": "Path", + "Desc": "Name of file containing BeamDyn input parameters for blade 3 (quoted string)", + "Line": 36, + "Value": "FileNotFound", + "FileType": "BeamDyn", + "Root": false + }, + "InflowFile": { + "Name": "InflowFile", + "Type": "Path", + "Desc": "Name of file containing inflow wind input parameters (quoted string)", + "Line": 37, + "Value": "NREL_5MW_InflowWind.dat", + "FileType": "InflowWind", + "Root": false + }, + "AeroFile": { + "Name": "AeroFile", + "Type": "Path", + "Desc": "Name of file containing aerodynamic input parameters (quoted string)", + "Line": 38, + "Value": "NREL_5MW_Monopile_AeroDyn15.dat", + "FileType": "AeroDyn", + "Root": false + }, + "ServoFile": { + "Name": "ServoFile", + "Type": "Path", + "Desc": "Name of file containing control and electrical-drive input parameters (quoted string)", + "Line": 39, + "Value": "NREL_5MW_Monopile_ServoDyn.dat", + "FileType": "ServoDyn", + "Root": false + }, + "HydroFile": { + "Name": "HydroFile", + "Type": "Path", + "Desc": "Name of file containing hydrodynamic input parameters (quoted string)", + "Line": 40, + "Value": "NREL_5MW_Monopile_HydroDyn.dat", + "FileType": "HydroDyn", + "Root": false + }, + "SubFile": { + "Name": "SubFile", + "Type": "Path", + "Desc": "Name of file containing sub-structural input parameters (quoted string)", + "Line": 41, + "Value": "NREL_5MW_Monopile_SubDyn.dat", + "FileType": "SubDyn", + "Root": false + }, + "MooringFile": { + "Name": "MooringFile", + "Type": "Path", + "Desc": "Name of file containing mooring system input parameters (quoted string)", + "Line": 42, + "Value": "FileNotFound", + "FileType": "Misc", + "Root": false + }, + "IceFile": { + "Name": "IceFile", + "Type": "Path", + "Desc": "Name of file containing ice input parameters (quoted string)", + "Line": 43, + "Value": "FileNotFound", + "FileType": "Misc", + "Root": false + }, + "SttsTime": { + "Name": "SttsTime", + "Type": "Real", + "Desc": "Amount of time between screen status messages (s)", + "Line": 46, + "Value": 1 + }, + "OutFileFmt": { + "Name": "OutFileFmt", + "Type": "Integer", + "Desc": "Format for tabular (time-marching) output file (switch) {0: uncompressed binary [\u003cRootName\u003e.outb], 1: text file [\u003cRootName\u003e.out], 2: binary file [\u003cRootName\u003e.outb], 3: both 1 and 2}", + "Line": 50, + "Value": 0, + "Size": false + }, + "OutFmt": { + "Name": "OutFmt", + "Type": "String", + "Desc": "Format used for text tabular output, excluding the time channel. Resulting field should be 10 characters. (quoted string)", + "Line": 52, + "Value": "ES18.9E3" + }, + "Linearize": { + "Name": "Linearize", + "Type": "Bool", + "Desc": "Linearization analysis (flag)", + "Line": 54, + "Value": true + }, + "CalcSteady": { + "Name": "CalcSteady", + "Type": "Bool", + "Desc": "Calculate a steady-state periodic operating point before linearization? [unused if Linearize=False] (flag)", + "Line": 55, + "Value": true + }, + "TrimCase": { + "Name": "TrimCase", + "Type": "Integer", + "Desc": "Controller parameter to be trimmed {1:yaw; 2:torque; 3:pitch} [used only if CalcSteady=True] (-)", + "Line": 56, + "Value": 3, + "Size": false + }, + "TrimTol": { + "Name": "TrimTol", + "Type": "Real", + "Desc": "Tolerance for the rotational speed convergence [used only if CalcSteady=True] (-)", + "Line": 57, + "Value": 0.001 + }, + "TrimGain": { + "Name": "TrimGain", + "Type": "Real", + "Desc": "Proportional gain for the rotational speed error (\u003e0) [used only if CalcSteady=True] (rad/(rad/s) for yaw or pitch; Nm/(rad/s) for torque)", + "Line": 58, + "Value": 0.01 + }, + "Twr_Kdmp": { + "Name": "Twr_Kdmp", + "Type": "Real", + "Desc": "Damping factor for the tower [used only if CalcSteady=True] (N/(m/s))", + "Line": 59, + "Value": 100 + }, + "Bld_Kdmp": { + "Name": "Bld_Kdmp", + "Type": "Real", + "Desc": "Damping factor for the blades [used only if CalcSteady=True] (N/(m/s))", + "Line": 60, + "Value": 100 + }, + "NLinTimes": { + "Name": "NLinTimes", + "Type": "Integer", + "Desc": "Number of times to linearize (-) [\u003e=1] [unused if Linearize=False]", + "Line": 61, + "Value": 36, + "Size": false + }, + "LinTimes": { + "Name": "LinTimes", + "Type": "Reals", + "Desc": "List of times at which to linearize (s) [1 to NLinTimes] [used only when Linearize=True and CalcSteady=False]", + "Line": 62, + "Value": [ + 30, + 60 + ] + }, + "LinInputs": { + "Name": "LinInputs", + "Type": "Integer", + "Desc": "Inputs included in linearization (switch) {0=none; 1=standard; 2=all module inputs (debug)} [unused if Linearize=False]", + "Line": 63, + "Value": 1, + "Size": false + }, + "LinOutputs": { + "Name": "LinOutputs", + "Type": "Integer", + "Desc": "Outputs included in linearization (switch) {0=none; 1=from OutList(s); 2=all module outputs (debug)} [unused if Linearize=False]", + "Line": 64, + "Value": 1, + "Size": false + }, + "LinOutJac": { + "Name": "LinOutJac", + "Type": "Bool", + "Desc": "Include full Jacobians in linearization output (for debug) (flag) [unused if Linearize=False; used only if LinInputs=LinOutputs=2]", + "Line": 65, + "Value": false + }, + "LinOutMod": { + "Name": "LinOutMod", + "Type": "Bool", + "Desc": "Write module-level linearization output files in addition to output for full system? (flag) [unused if Linearize=False]", + "Line": 66, + "Value": false + }, + "WrVTK": { + "Name": "WrVTK", + "Type": "Integer", + "Desc": "VTK visualization data output: (switch) {0=none; 1=initialization data only; 2=animation; 3=mode shapes}", + "Line": 68, + "Value": 0, + "Size": false + }, + "VTK_type": { + "Name": "VTK_type", + "Type": "Integer", + "Desc": "Type of VTK visualization data: (switch) {1=surfaces; 2=basic meshes (lines/points); 3=all meshes (debug)} [unused if WrVTK=0]", + "Line": 69, + "Value": 2, + "Size": false + }, + "VTK_fps": { + "Name": "VTK_fps", + "Type": "Integer", + "Desc": "Frame rate for VTK output (frames per second){will use closest integer multiple of DT} [used only if WrVTK=2 or WrVTK=3]", + "Line": 71, + "Value": 15, + "Size": false + } + } + ], + "ElastoDyn": [ + { + "Name": "NREL_5MW_Monopile_ElastoDyn.dat", + "Type": "ElastoDyn", + "Lines": [ + "------- ELASTODYN for OpenFAST INPUT FILE -------------------------------------------", + "NREL 5.0 MW Baseline Wind Turbine for Use in Offshore Analysis. Properties from Dutch Offshore Wind Energy Converter (DOWEC) 6MW Pre-Design (10046_009.pdf) and REpower 5M 5MW (5m_uk.pdf);", + "---------------------- SIMULATION CONTROL --------------------------------------", + "False Echo - Echo input data to \"\u003cRootName\u003e.ech\" (flag)", + " 3 Method - Integration method: {1: RK4, 2: AB4, or 3: ABM4} (-)", + "\"default\" DT - Integration time step (s)", + "---------------------- DEGREES OF FREEDOM --------------------------------------", + "True FlapDOF1 - First flapwise blade mode DOF (flag)", + "True FlapDOF2 - Second flapwise blade mode DOF (flag)", + "True EdgeDOF - First edgewise blade mode DOF (flag)", + "False TeetDOF - Rotor-teeter DOF (flag) [unused for 3 blades]", + "True DrTrDOF - Drivetrain rotational-flexibility DOF (flag)", + "True GenDOF - Generator DOF (flag)", + "True YawDOF - Yaw DOF (flag)", + "True TwFADOF1 - First fore-aft tower bending-mode DOF (flag)", + "True TwFADOF2 - Second fore-aft tower bending-mode DOF (flag)", + "True TwSSDOF1 - First side-to-side tower bending-mode DOF (flag)", + "True TwSSDOF2 - Second side-to-side tower bending-mode DOF (flag)", + "True PtfmSgDOF - Platform horizontal surge translation DOF (flag)", + "True PtfmSwDOF - Platform horizontal sway translation DOF (flag)", + "True PtfmHvDOF - Platform vertical heave translation DOF (flag)", + "True PtfmRDOF - Platform roll tilt rotation DOF (flag)", + "True PtfmPDOF - Platform pitch tilt rotation DOF (flag)", + "True PtfmYDOF - Platform yaw rotation DOF (flag)", + "---------------------- INITIAL CONDITIONS --------------------------------------", + " 0 OoPDefl - Initial out-of-plane blade-tip displacement (meters)", + " 0 IPDefl - Initial in-plane blade-tip deflection (meters)", + " 0 BlPitch(1) - Blade 1 initial pitch (degrees)", + " 0 BlPitch(2) - Blade 2 initial pitch (degrees)", + " 0 BlPitch(3) - Blade 3 initial pitch (degrees) [unused for 2 blades]", + " 0 TeetDefl - Initial or fixed teeter angle (degrees) [unused for 3 blades]", + " 0 Azimuth - Initial azimuth angle for blade 1 (degrees)", + " 12.1 RotSpeed - Initial or fixed rotor speed (rpm)", + " 0 NacYaw - Initial or fixed nacelle-yaw angle (degrees)", + " 0 TTDspFA - Initial fore-aft tower-top displacement (meters)", + " 0 TTDspSS - Initial side-to-side tower-top displacement (meters)", + " 0 PtfmSurge - Initial or fixed horizontal surge translational displacement of platform (meters)", + " 0 PtfmSway - Initial or fixed horizontal sway translational displacement of platform (meters)", + " -0.0009 PtfmHeave - Initial or fixed vertical heave translational displacement of platform (meters)", + " 0 PtfmRoll - Initial or fixed roll tilt rotational displacement of platform (degrees)", + " 0 PtfmPitch - Initial or fixed pitch tilt rotational displacement of platform (degrees)", + " 0 PtfmYaw - Initial or fixed yaw rotational displacement of platform (degrees)", + "---------------------- TURBINE CONFIGURATION -----------------------------------", + " 3 NumBl - Number of blades (-)", + " 63 TipRad - The distance from the rotor apex to the blade tip (meters)", + " 1.5 HubRad - The distance from the rotor apex to the blade root (meters)", + " -2.5 PreCone(1) - Blade 1 cone angle (degrees)", + " -2.5 PreCone(2) - Blade 2 cone angle (degrees)", + " -2.5 PreCone(3) - Blade 3 cone angle (degrees) [unused for 2 blades]", + " 0 HubCM - Distance from rotor apex to hub mass [positive downwind] (meters)", + " 0 UndSling - Undersling length [distance from teeter pin to the rotor apex] (meters) [unused for 3 blades]", + " 0 Delta3 - Delta-3 angle for teetering rotors (degrees) [unused for 3 blades]", + " 0 AzimB1Up - Azimuth value to use for I/O when blade 1 points up (degrees)", + " -5.0191 OverHang - Distance from yaw axis to rotor apex [3 blades] or teeter pin [2 blades] (meters)", + " 1.912 ShftGagL - Distance from rotor apex [3 blades] or teeter pin [2 blades] to shaft strain gages [positive for upwind rotors] (meters)", + " -5 ShftTilt - Rotor shaft tilt angle (degrees)", + " 1.9 NacCMxn - Downwind distance from the tower-top to the nacelle CM (meters)", + " 0 NacCMyn - Lateral distance from the tower-top to the nacelle CM (meters)", + " 1.75 NacCMzn - Vertical distance from the tower-top to the nacelle CM (meters)", + " -3.09528 NcIMUxn - Downwind distance from the tower-top to the nacelle IMU (meters)", + " 0 NcIMUyn - Lateral distance from the tower-top to the nacelle IMU (meters)", + " 2.23336 NcIMUzn - Vertical distance from the tower-top to the nacelle IMU (meters)", + " 1.96256 Twr2Shft - Vertical distance from the tower-top to the rotor shaft (meters)", + " 87.6 TowerHt - Height of tower relative to ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] (meters)", + " 10 TowerBsHt - Height of tower base relative to ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] (meters)", + " 0 PtfmCMxt - Downwind distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform CM (meters)", + " 0 PtfmCMyt - Lateral distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform CM (meters)", + " 10 PtfmCMzt - Vertical distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform CM (meters)", + " 10 PtfmRefzt - Vertical distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform reference point (meters)", + "---------------------- MASS AND INERTIA ----------------------------------------", + " 0 TipMass(1) - Tip-brake mass, blade 1 (kg)", + " 0 TipMass(2) - Tip-brake mass, blade 2 (kg)", + " 0 TipMass(3) - Tip-brake mass, blade 3 (kg) [unused for 2 blades]", + " 56780 HubMass - Hub mass (kg)", + " 115926 HubIner - Hub inertia about rotor axis [3 blades] or teeter axis [2 blades] (kg m^2)", + " 534.116 GenIner - Generator inertia about HSS (kg m^2)", + " 240000 NacMass - Nacelle mass (kg)", + "2.60789E+06 NacYIner - Nacelle inertia about yaw axis (kg m^2)", + " 0 YawBrMass - Yaw bearing mass (kg)", + " 0 PtfmMass - Platform mass (kg)", + " 0 PtfmRIner - Platform inertia for roll tilt rotation about the platform CM (kg m^2)", + " 0 PtfmPIner - Platform inertia for pitch tilt rotation about the platform CM (kg m^2)", + " 1.534E+06 PtfmYIner - Platform inertia for yaw rotation about the platform CM (kg m^2)", + "---------------------- BLADE ---------------------------------------------------", + " 17 BldNodes - Number of blade nodes (per blade) used for analysis (-)", + "\"NREL_5MW_ElastoDyn_Blade.dat\" BldFile(1) - Name of file containing properties for blade 1 (quoted string)", + "\"NREL_5MW_ElastoDyn_Blade.dat\" BldFile(2) - Name of file containing properties for blade 2 (quoted string)", + "\"NREL_5MW_ElastoDyn_Blade.dat\" BldFile(3) - Name of file containing properties for blade 3 (quoted string) [unused for 2 blades]", + "---------------------- ROTOR-TEETER --------------------------------------------", + " 0 TeetMod - Rotor-teeter spring/damper model {0: none, 1: standard, 2: user-defined from routine UserTeet} (switch) [unused for 3 blades]", + " 0 TeetDmpP - Rotor-teeter damper position (degrees) [used only for 2 blades and when TeetMod=1]", + " 0 TeetDmp - Rotor-teeter damping constant (N-m/(rad/s)) [used only for 2 blades and when TeetMod=1]", + " 0 TeetCDmp - Rotor-teeter rate-independent Coulomb-damping moment (N-m) [used only for 2 blades and when TeetMod=1]", + " 0 TeetSStP - Rotor-teeter soft-stop position (degrees) [used only for 2 blades and when TeetMod=1]", + " 0 TeetHStP - Rotor-teeter hard-stop position (degrees) [used only for 2 blades and when TeetMod=1]", + " 0 TeetSSSp - Rotor-teeter soft-stop linear-spring constant (N-m/rad) [used only for 2 blades and when TeetMod=1]", + " 0 TeetHSSp - Rotor-teeter hard-stop linear-spring constant (N-m/rad) [used only for 2 blades and when TeetMod=1]", + "---------------------- DRIVETRAIN ----------------------------------------------", + " 100 GBoxEff - Gearbox efficiency (%)", + " 97 GBRatio - Gearbox ratio (-)", + "8.67637E+08 DTTorSpr - Drivetrain torsional spring (N-m/rad)", + " 6.215E+06 DTTorDmp - Drivetrain torsional damper (N-m/(rad/s))", + "---------------------- FURLING -------------------------------------------------", + "False Furling - Read in additional model properties for furling turbine (flag) [must currently be FALSE)", + "\"unused\" FurlFile - Name of file containing furling properties (quoted string) [unused when Furling=False]", + "---------------------- TOWER ---------------------------------------------------", + " 20 TwrNodes - Number of tower nodes used for analysis (-)", + "\"NREL_5MW_Monopile_ElastoDyn_Tower.dat\" TwrFile - Name of file containing tower properties (quoted string)", + "---------------------- OUTPUT --------------------------------------------------", + "True SumPrint - Print summary data to \"\u003cRootName\u003e.sum\" (flag)", + " 1 OutFile - Switch to determine where output will be placed: {1: in module output file only; 2: in glue code output file only; 3: both} (currently unused)", + "True TabDelim - Use tab delimiters in text tabular output file? (flag) (currently unused)", + "\"ES10.3E2\" OutFmt - Format used for text tabular output (except time). Resulting field should be 10 characters. (quoted string) (currently unused)", + " 0 TStart - Time to begin tabular output (s) (currently unused)", + " 1 DecFact - Decimation factor for tabular output {1: output every time step} (-) (currently unused)", + " 1 NTwGages - Number of tower nodes that have strain gages for output [0 to 9] (-)", + " 20 TwrGagNd - List of tower nodes that have strain gages [1 to TwrNodes] (-) [unused if NTwGages=0]", + " 3 NBlGages - Number of blade nodes that have strain gages for output [0 to 9] (-)", + " 5, 9, 13 BldGagNd - List of blade nodes that have strain gages [1 to BldNodes] (-) [unused if NBlGages=0]", + " OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-)", + "\"OoPDefl1, IPDefl1, TwstDefl1\" - Blade 1 out-of-plane and in-plane deflections and tip twist", + "\"BldPitch1\" - Blade 1 pitch angle", + "\"Azimuth\" - Blade 1 azimuth angle", + "\"RotSpeed, GenSpeed\" - Low-speed shaft and high-speed shaft speeds", + "\"TwHt1TPxi, TwHt1TPyi, TTDspTwst\" - Tower fore-aft and side-to-side displacements and top twist", + "\"PtfmSurge, PtfmSway\" - Platform horizontal surge displacement", + "\"PtfmRoll , PtfmPitch\" - Platform rotational displacements", + "\"Spn2MLxb1, Spn2MLyb1\" - Blade 1 local edgewise and flapwise bending moments at span station 2 (approx. 50% span)", + "\"RootFxc1, RootFyc1, RootFzc1\" - Out-of-plane shear, in-plane shear, and axial forces at the root of blade 1", + "\"RootMxc1, RootMyc1, RootMzc1\" - In-plane bending, out-of-plane bending, and pitching moments at the root of blade 1", + "\"RotTorq, LSSGagMya, LSSGagMza\" - Rotor torque and low-speed shaft 0- and 90-bending moments at the main bearing", + "\"YawBrFxp, YawBrFyp, YawBrFzp\" - Fore-aft shear, side-to-side shear, and vertical forces at the top of the tower (not rotating with nacelle yaw)", + "\"YawBrMxp, YawBrMyp, YawBrMzp\" - Side-to-side bending, fore-aft bending, and yaw moments at the top of the tower (not rotating with nacelle yaw)", + "END of input file (the word \"END\" must appear in the first 3 columns of this last OutList line)", + "---------------------------------------------------------------------------------------" + ], + "FlapDOF1": { + "Name": "FlapDOF1", + "Type": "Bool", + "Desc": "First flapwise blade mode DOF (flag)", + "Line": 8, + "Value": true + }, + "FlapDOF2": { + "Name": "FlapDOF2", + "Type": "Bool", + "Desc": "Second flapwise blade mode DOF (flag)", + "Line": 9, + "Value": true + }, + "EdgeDOF": { + "Name": "EdgeDOF", + "Type": "Bool", + "Desc": "First edgewise blade mode DOF (flag)", + "Line": 10, + "Value": true + }, + "TeetDOF": { + "Name": "TeetDOF", + "Type": "Bool", + "Desc": "Rotor-teeter DOF (flag) [unused for 3 blades]", + "Line": 11, + "Value": false + }, + "DrTrDOF": { + "Name": "DrTrDOF", + "Type": "Bool", + "Desc": "Drivetrain rotational-flexibility DOF (flag)", + "Line": 12, + "Value": true + }, + "GenDOF": { + "Name": "GenDOF", + "Type": "Bool", + "Desc": "Generator DOF (flag)", + "Line": 13, + "Value": true + }, + "YawDOF": { + "Name": "YawDOF", + "Type": "Bool", + "Desc": "Yaw DOF (flag)", + "Line": 14, + "Value": false + }, + "TwFADOF1": { + "Name": "TwFADOF1", + "Type": "Bool", + "Desc": "First fore-aft tower bending-mode DOF (flag)", + "Line": 15, + "Value": true + }, + "TwFADOF2": { + "Name": "TwFADOF2", + "Type": "Bool", + "Desc": "Second fore-aft tower bending-mode DOF (flag)", + "Line": 16, + "Value": true + }, + "TwSSDOF1": { + "Name": "TwSSDOF1", + "Type": "Bool", + "Desc": "First side-to-side tower bending-mode DOF (flag)", + "Line": 17, + "Value": true + }, + "TwSSDOF2": { + "Name": "TwSSDOF2", + "Type": "Bool", + "Desc": "Second side-to-side tower bending-mode DOF (flag)", + "Line": 18, + "Value": true + }, + "BlPitch1": { + "Name": "BlPitch(1)", + "Type": "Real", + "Desc": "Blade 1 initial pitch (degrees)", + "Line": 28, + "Value": 0 + }, + "BlPitch2": { + "Name": "BlPitch(2)", + "Type": "Real", + "Desc": "Blade 2 initial pitch (degrees)", + "Line": 29, + "Value": 0 + }, + "BlPitch3": { + "Name": "BlPitch(3)", + "Type": "Real", + "Desc": "Blade 3 initial pitch (degrees) [unused for 2 blades]", + "Line": 30, + "Value": 0 + }, + "RotSpeed": { + "Name": "RotSpeed", + "Type": "Real", + "Desc": "Initial or fixed rotor speed (rpm)", + "Line": 33, + "Value": 12.1 + }, + "NumBl": { + "Name": "NumBl", + "Type": "Integer", + "Desc": "Number of blades (-)", + "Line": 44, + "Value": 3, + "Size": false + }, + "ShftTilt": { + "Name": "ShftTilt", + "Type": "Real", + "Desc": "Rotor shaft tilt angle (degrees)", + "Line": 56, + "Value": -5 + }, + "BldFile1": { + "Name": "BldFile(1)", + "Type": "Path", + "Desc": "Name of file containing properties for blade 1 (quoted string)", + "Line": 86, + "Value": "NREL_5MW_ElastoDyn_Blade.dat", + "FileType": "Misc", + "Root": false + }, + "BldFile2": { + "Name": "BldFile(2)", + "Type": "Path", + "Desc": "Name of file containing properties for blade 2 (quoted string)", + "Line": 87, + "Value": "NREL_5MW_ElastoDyn_Blade.dat", + "FileType": "Misc", + "Root": false + }, + "BldFile3": { + "Name": "BldFile(3)", + "Type": "Path", + "Desc": "Name of file containing properties for blade 3 (quoted string) [unused for 2 blades]", + "Line": 88, + "Value": "NREL_5MW_ElastoDyn_Blade.dat", + "FileType": "Misc", + "Root": false + }, + "TwrFile": { + "Name": "TwrFile", + "Type": "Path", + "Desc": "Name of file containing tower properties (quoted string)", + "Line": 108, + "Value": "NREL_5MW_Monopile_ElastoDyn_Tower.dat", + "FileType": "Misc", + "Root": false + } + } + ], + "BeamDyn": [], + "SubDyn": [ + { + "Name": "NREL_5MW_Monopile_SubDyn.dat", + "Type": "SubDyn", + "Lines": [ + "----------- SubDyn MultiMember Support Structure Input File ---------------------------", + "OC3 Monopile configuration (pile only).", + "-------------------------- SIMULATION CONTROL -----------------------------------------", + "False Echo - Echo input data to \"\u003crootname\u003e.SD.ech\" (flag)", + "\"DEFAULT\" SDdeltaT - Local Integration Step. If \"default\", the glue-code integration step will be used.", + " 3 IntMethod - Integration Method [1/2/3/4 = RK4/AB4/ABM4/AM2].", + "True SttcSolve - Solve dynamics about static equilibrium point", + "False GuyanLoadCorrection - Include extra moment from lever arm at interface and rotate FEM for floating.", + "-------------------- FEA and CRAIG-BAMPTON PARAMETERS ---------------------------------", + " 3 FEMMod - FEM switch: element model in the FEM. [1= Euler-Bernoulli(E-B); 2=Tapered E-B (unavailable); 3= 2-node Timoshenko; 4= 2-node tapered Timoshenko (unavailable)]", + " 3 NDiv - Number of sub-elements per member", + "True CBMod - [T/F] If True perform C-B reduction, else full FEM dofs will be retained. If True, select Nmodes to retain in C-B reduced system.", + " 0 Nmodes - Number of internal modes to retain (ignored if CBMod=False). If Nmodes=0 --\u003e Guyan Reduction.", + " 1 JDampings - Damping Ratios for each retained mode (% of critical) If Nmodes\u003e0, list Nmodes structural damping ratios for each retained mode (% of critical), or a single damping ratio to be applied to all retained modes. (last entered value will be used for all remaining modes).", + " 2 GuyanDampMod - Guyan damping {0=none, 1=Rayleigh Damping, 2=user specified 6x6 matrix}", + " 0.000, 0.000 RayleighDamp - Mass and stiffness proportional damping coefficients (Rayleigh Damping) [only if GuyanDampMod=1]", + " 6 GuyanDampSize - Guyan damping matrix (6x6) [only if GuyanDampMod=2]", + " 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00", + " 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00", + " 0.0000e+00 0.0000e+00 1.4625e+06 0.0000e+00 0.0000e+00 0.0000e+00", + " 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00", + " 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00", + " 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00", + "---- STRUCTURE JOINTS: joints connect structure members (~Hydrodyn Input File) --------", + " 4 NJoints - Number of joints (-)", + "JointID JointXss JointYss JointZss JointType JointDirX JointDirY JointDirZ JointStiff ![Coordinates of Member joints in SS-Coordinate System][JointType={1:cantilever, 2:universal joint, 3:revolute joint, 4:spherical joint}]", + " (-) (m) (m) (m) (-) (-) (-) (-) (Nm/rad) ", + " 1 0.00000 0.00000 -20.00010 1 0.0 0.0 0.0 0.0 ", + " 2 0.00000 0.00000 -10.00000 1 0.0 0.0 0.0 0.0 ", + " 3 0.00000 0.00000 0.00000 1 0.0 0.0 0.0 0.0 ", + " 4 0.00000 0.00000 10.00000 1 0.0 0.0 0.0 0.0 ", + "------------------- BASE REACTION JOINTS: 1/0 for Locked/Free DOF @ each Reaction Node ---------------------", + " 1 NReact - Number of Joints with reaction forces; be sure to remove all rigid motion DOFs of the structure (else det([K])=[0])", + "RJointID RctTDXss RctTDYss RctTDZss RctRDXss RctRDYss RctRDZss SSIfile ![Global Coordinate System]", + " (-) (flag) (flag) (flag) (flag) (flag) (flag) (string)", + " 1 1 1 1 1 1 1 \"\"", + "------- INTERFACE JOINTS: 1/0 for Locked (to the TP)/Free DOF @each Interface Joint (only Locked-to-TP implemented thus far (=rigid TP)) ---------", + " 1 NInterf - Number of interface joints locked to the Transition Piece (TP): be sure to remove all rigid motion dofs", + "IJointID ItfTDXss ItfTDYss ItfTDZss ItfRDXss ItfRDYss ItfRDZss ![Global Coordinate System]", + " (-) (flag) (flag) (flag) (flag) (flag) (flag)", + " 4 1 1 1 1 1 1", + "----------------------------------- MEMBERS -------------------------------------------", + " 3 NMembers - Number of members (-)", + "MemberID MJointID1 MJointID2 MPropSetID1 MPropSetID2 MType COSMID ![MType={1:beam circ., 2:cable, 3:rigid, 4:beam arb.}. COMSID={-1:none}]", + " (-) (-) (-) (-) (-) (-) (-)", + " 1 1 2 1 1 1 -1", + " 2 2 3 1 1 1 -1", + " 3 3 4 1 1 1 -1", + "------------------ CIRCULAR BEAM CROSS-SECTION PROPERTIES -----------------------------", + " 4 NPropSets - Number of structurally unique cross-sections", + "PropSetID YoungE ShearG MatDens XsecD XsecT", + " (-) (N/m2) (N/m2) (kg/m3) (m) (m)", + " 1 2.10000e+11 8.08000e+10 8500.00 6.000000 0.060000", + " 2 2.10000e+11 8.08000e+10 8500.00 6.000000 0.027000", + " 3 2.10000e+11 8.08000e+10 8500.00 3.870000 0.019000", + " 4 2.10000e+14 8.08000e+14 1.00 1.000000 0.010000", + "----------------- ARBITRARY BEAM CROSS-SECTION PROPERTIES -----------------------------", + " 0 NXPropSets - Number of structurally unique non-circular cross-sections (if 0 the following table is ignored)", + "PropSetID YoungE ShearG MatDens XsecA XsecAsx XsecAsy XsecJxx XsecJyy XsecJ0", + " (-) (N/m2) (N/m2) (kg/m3) (m2) (m2) (m2) (m4) (m4) (m4)", + "-------------------------- CABLE PROPERTIES -------------------------------------------", + " 0 NCablePropSets - Number of cable cable properties", + "PropSetID EA MatDens T0 CtrlChannel", + " (-) (N) (kg/m) (N) (-)", + "----------------------- RIGID LINK PROPERTIES -----------------------------------------", + " 0 NRigidPropSets - Number of rigid link properties", + "PropSetID MatDens ", + " (-) (kg/m)", + "---------------------- MEMBER COSINE MATRICES COSM(i,j) -------------------------------", + " 0 NCOSMs - Number of unique cosine matrices (i.e., of unique member alignments including principal axis rotations); ignored if NXPropSets=0 or 9999 in any element below", + "COSMID COSM11 COSM12 COSM13 COSM21 COSM22 COSM23 COSM31 COSM32 COSM33", + " (-) (-) (-) (-) (-) (-) (-) (-) (-) (-)", + "------------------------ JOINT ADDITIONAL CONCENTRATED MASSES--------------------------", + " 0 NCmass - Number of joints with concentrated masses; Global Coordinate System", + "CMJointID JMass JMXX JMYY JMZZ JMXY JMXZ JMYZ MCGX MCGY MCGZ", + " (-) (kg) (kg*m^2) (kg*m^2) (kg*m^2) (kg*m^2) (kg*m^2) (kg*m^2) (m) (m) (m)", + "---------------------------- OUTPUT: SUMMARY \u0026 OUTFILE --------------------------------", + "True SumPrint - Output a Summary File (flag)", + "0 OutCBModes - Output Guyan and Craig-Bampton modes {0: No output, 1: JSON output}, (flag)", + "0 OutFEMModes - Output first 30 FEM modes {0: No output, 1: JSON output} (flag)", + "False OutCOSM - Output cosine matrices with the selected output member forces (flag)", + "False OutAll - [T/F] Output all members' end forces", + " 2 OutSwtch - [1/2/3] Output requested channels to: 1=\u003crootname\u003e.SD.out; 2=\u003crootname\u003e.out (generated by FAST); 3=both files.", + "True TabDelim - Generate a tab-delimited output in the \u003crootname\u003e.SD.out file", + " 1 OutDec - Decimation of output in the \u003crootname\u003e.SD.out file", + "\"ES11.4e2\" OutFmt - Output format for numerical results in the \u003crootname\u003e.SD.out file", + "\"A11\" OutSFmt - Output format for header strings in the \u003crootname\u003e.SD.out file", + "------------------------- MEMBER OUTPUT LIST ------------------------------------------", + " 2 NMOutputs - Number of members whose forces/displacements/velocities/accelerations will be output (-) [Must be \u003c= 99].", + "MemberID NOutCnt NodeCnt ![NOutCnt=how many nodes to get output for [\u003c 10]; NodeCnt are local ordinal numbers from the start of the member, and must be \u003e=1 and \u003c= NDiv+1] If NMOutputs=0 leave blank as well.", + " (-) (-) (-)", + " 2 1 1", + " 3 1 1", + "------------------------- SSOutList: The next line(s) contains a list of output parameters that will be output in \u003crootname\u003e.SD.out or \u003crootname\u003e.out. ------", + "\"M2N1MKxe, M2N1MKye\" - The local side-to-side and fore-aft bending moments at node 1 of member 3 (located at 0 m, i.e. MSL).", + "\"M1N1MKxe, M1N1MKye\" - The local side-to-side and fore-aft bending moments at node 1 of member 2 (located at -10 m, i.e. half way between MSL and mudline).", + "\"-ReactFXss, -ReactFYss, -ReactFZss\" - Base reactions: fore-aft shear, side-to-side shear and vertical forces at the mudline.", + "\"-ReactMXss, -ReactMYss, -ReactMZss\" - Base reactions: side-to-side, fore-aft and yaw moments at the mudline.", + "END of output channels and end of file. (the word \"END\" must appear in the first 3 columns of this line)" + ], + "CBMod": { + "Name": "CBMod", + "Type": "Bool", + "Desc": "[T/F] If True perform C-B reduction, else full FEM dofs will be retained. If True, select Nmodes to retain in C-B reduced system.", + "Line": 12, + "Value": true + }, + "Nmodes": { + "Name": "Nmodes", + "Type": "Integer", + "Desc": "Number of internal modes to retain (ignored if CBMod=False). If Nmodes=0 --\u003e Guyan Reduction.", + "Line": 13, + "Value": 0, + "Size": false + } + } + ], + "AeroDyn": [ + { + "Name": "NREL_5MW_Monopile_AeroDyn15.dat", + "Type": "AeroDyn", + "Lines": [ + "------- AERODYN v15 for OpenFAST INPUT FILE -----------------------------------------------", + "NREL 5.0 MW offshore baseline aerodynamic input properties, with OC3 Monopile tower", + "====== General Options ============================================================================", + "False Echo - Echo the input to \"\u003crootname\u003e.AD.ech\"? (flag)", + "\"default\" DTAero - Time interval for aerodynamic calculations {or \"default\"} (s)", + " 1 WakeMod - Type of wake/induction model (switch) {0=none, 1=BEMT, 2=DBEMT, 3=OLAF} [WakeMod cannot be 2 or 3 when linearizing]", + " 2 AFAeroMod - Type of blade airfoil aerodynamics model (switch) {1=steady model, 2=Beddoes-Leishman unsteady model} [AFAeroMod must be 1 when linearizing]", + " 1 TwrPotent - Type tower influence on wind based on potential flow around the tower (switch) {0=none, 1=baseline potential flow, 2=potential flow with Bak correction}", + " 0 TwrShadow - Calculate tower influence on wind based on downstream tower shadow (switch) {0=none, 1=Powles model, 2=Eames model}", + "True TwrAero - Calculate tower aerodynamic loads? (flag)", + "False FrozenWake - Assume frozen wake during linearization? (flag) [used only when WakeMod=1 and when linearizing]", + "False CavitCheck - Perform cavitation check? (flag) [AFAeroMod must be 1 when CavitCheck=true]", + "False Buoyancy - Include buoyancy effects? (flag)", + "False CompAA - Flag to compute AeroAcoustics calculation [used only when WakeMod = 1 or 2]", + "\"unused\" AA_InputFile - AeroAcoustics input file [used only when CompAA=true]", + "====== Environmental Conditions ===================================================================", + "\"default\" AirDens - Air density (kg/m^3)", + "\"default\" KinVisc - Kinematic viscosity of working fluid (m^2/s)", + "\"default\" SpdSound - Speed of sound in working fluid (m/s)", + "\"default\" Patm - Atmospheric pressure (Pa) [used only when CavitCheck=True]", + "\"default\" Pvap - Vapour pressure of working fluid (Pa) [used only when CavitCheck=True]", + "====== Blade-Element/Momentum Theory Options ====================================================== [unused when WakeMod=0 or 3]", + " 2 SkewMod - Type of skewed-wake correction model (switch) {1=uncoupled, 2=Pitt/Peters, 3=coupled} [unused when WakeMod=0 or 3]", + "\"default\" SkewModFactor - Constant used in Pitt/Peters skewed wake model {or \"default\" is 15/32*pi} (-) [used only when SkewMod=2; unused when WakeMod=0 or 3]", + "True TipLoss - Use the Prandtl tip-loss model? (flag) [unused when WakeMod=0 or 3]", + "True HubLoss - Use the Prandtl hub-loss model? (flag) [unused when WakeMod=0 or 3]", + "True TanInd - Include tangential induction in BEMT calculations? (flag) [unused when WakeMod=0 or 3]", + "False AIDrag - Include the drag term in the axial-induction calculation? (flag) [unused when WakeMod=0 or 3]", + "False TIDrag - Include the drag term in the tangential-induction calculation? (flag) [unused when WakeMod=0,3 or TanInd=FALSE]", + "\"Default\" IndToler - Convergence tolerance for BEMT nonlinear solve residual equation {or \"default\"} (-) [unused when WakeMod=0 or 3]", + " 100 MaxIter - Maximum number of iteration steps (-) [unused when WakeMod=0]", + "====== Dynamic Blade-Element/Momentum Theory Options ============================================== [used only when WakeMod=2]", + " 2 DBEMT_Mod - Type of dynamic BEMT (DBEMT) model {1=constant tau1, 2=time-dependent tau1, 3=constant tau1 with continuous formulation} (-) [used only when WakeMod=2]", + " 4 tau1_const - Time constant for DBEMT (s) [used only when WakeMod=2 and DBEMT_Mod=1 or 3]", + "====== OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options ================== [used only when WakeMod=3]", + "\"unused\" OLAFInputFileName - Input file for OLAF [used only when WakeMod=3]", + "====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2]", + " 3 UAMod - Unsteady Aero Model Switch (switch) {2=B-L Gonzalez, 3=B-L Minnema/Pierce, 4=B-L HGM 4-states, 5=B-L 5 states, 6=Oye, 7=Boeing-Vertol} [used only when AFAeroMod=2]", + "True FLookup - Flag to indicate whether a lookup for f' will be calculated (TRUE) or whether best-fit exponential equations will be used (FALSE); if FALSE S1-S4 must be provided in airfoil input files (flag) [used only when AFAeroMod=2]", + "====== Airfoil Information =========================================================================", + " 1 AFTabMod - Interpolation method for multiple airfoil tables {1=1D interpolation on AoA (first table only); 2=2D interpolation on AoA and Re; 3=2D interpolation on AoA and UserProp} (-)", + " 1 InCol_Alfa - The column in the airfoil tables that contains the angle of attack (-)", + " 2 InCol_Cl - The column in the airfoil tables that contains the lift coefficient (-)", + " 3 InCol_Cd - The column in the airfoil tables that contains the drag coefficient (-)", + " 4 InCol_Cm - The column in the airfoil tables that contains the pitching-moment coefficient; use zero if there is no Cm column (-)", + " 0 InCol_Cpmin - The column in the airfoil tables that contains the Cpmin coefficient; use zero if there is no Cpmin column (-)", + " 8 NumAFfiles - Number of airfoil files used (-)", + "\"Airfoils/Cylinder1.dat\" AFNames - Airfoil file names (NumAFfiles lines) (quoted strings)", + "\"Airfoils/Cylinder2.dat\"", + "\"Airfoils/DU40_A17.dat\"", + "\"Airfoils/DU35_A17.dat\"", + "\"Airfoils/DU30_A17.dat\"", + "\"Airfoils/DU25_A17.dat\"", + "\"Airfoils/DU21_A17.dat\"", + "\"Airfoils/NACA64_A17.dat\"", + "====== Rotor/Blade Properties =====================================================================", + "True UseBlCm - Include aerodynamic pitching moment in calculations? (flag)", + "\"NREL_5MW_AeroDyn_blade.dat\" ADBlFile(1) - Name of file containing distributed aerodynamic properties for Blade #1 (-)", + "\"NREL_5MW_AeroDyn_blade.dat\" ADBlFile(2) - Name of file containing distributed aerodynamic properties for Blade #2 (-) [unused if NumBl \u003c 2]", + "\"NREL_5MW_AeroDyn_blade.dat\" ADBlFile(3) - Name of file containing distributed aerodynamic properties for Blade #3 (-) [unused if NumBl \u003c 3]", + "====== Hub Properties ============================================================================== [used only when Buoyancy=True]", + "0.0 VolHub - Hub volume (m^3)", + "0.0 HubCenBx - Hub center of buoyancy x direction offset (m)", + "====== Nacelle Properties ========================================================================== [used only when Buoyancy=True]", + "0.0 VolNac - Nacelle volume (m^3)", + "0,0,0 NacCenB - Position of nacelle center of buoyancy from yaw bearing in nacelle coordinates (m)", + "====== Tail fin Aerodynamics ======================================================================== ", + "False TFinAero - Calculate tail fin aerodynamics model (flag)", + "\"unused\" TFinFile - Input file for tail fin aerodynamics [used only when TFinAero=True]", + "====== Tower Influence and Aerodynamics ============================================================ [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True]", + " 11 NumTwrNds - Number of tower nodes used in the analysis (-) [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True]", + "TwrElev TwrDiam TwrCd TwrTI TwrCb !TwrTI used only with TwrShadow=2, TwrCb used only with Buoyancy=True", + "(m) (m) (-) (-) (-)", + "1.0000000E+01 6.0000000E+00 1.0000000E+00 1.0000000E-01 0.0", + "1.7760000E+01 5.7870000E+00 1.0000000E+00 1.0000000E-01 0.0", + "2.5520000E+01 5.5740000E+00 1.0000000E+00 1.0000000E-01 0.0", + "3.3280000E+01 5.3610000E+00 1.0000000E+00 1.0000000E-01 0.0", + "4.1040000E+01 5.1480000E+00 1.0000000E+00 1.0000000E-01 0.0", + "4.8800000E+01 4.9350000E+00 1.0000000E+00 1.0000000E-01 0.0", + "5.6560000E+01 4.7220000E+00 1.0000000E+00 1.0000000E-01 0.0", + "6.4320000E+01 4.5090000E+00 1.0000000E+00 1.0000000E-01 0.0", + "7.2080000E+01 4.2960000E+00 1.0000000E+00 1.0000000E-01 0.0", + "7.9840000E+01 4.0830000E+00 1.0000000E+00 1.0000000E-01 0.0", + "8.7600000E+01 3.8700000E+00 1.0000000E+00 1.0000000E-01 0.0", + "====== Outputs ====================================================================================", + "True SumPrint - Generate a summary file listing input options and interpolated properties to \"\u003crootname\u003e.AD.sum\"? (flag)", + " 0 NBlOuts - Number of blade node outputs [0 - 9] (-)", + " 2, 9, 16, 4, 5, 7, 11, 13, 14 BlOutNd - Blade nodes whose values will be output (-)", + " 0 NTwOuts - Number of tower node outputs [0 - 9] (-)", + " 1, 2, 3, 4, 5 TwOutNd - Tower nodes whose values will be output (-)", + " OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-)", + "\"RtAeroFxh, RtAeroFyh, RtAeroFzh\" ", + "\"RtAeroMxh, RtAeroMyh, RtAeroMzh\" ", + "END of input file (the word \"END\" must appear in the first 3 columns of this last OutList line)", + "---------------------------------------------------------------------------------------" + ], + "WakeMod": { + "Name": "WakeMod", + "Type": "Integer", + "Desc": "Type of wake/induction model (switch) {0=none, 1=BEMT, 2=DBEMT, 3=OLAF} [WakeMod cannot be 2 or 3 when linearizing]", + "Line": 6, + "Value": 1, + "Size": false + }, + "AFAeroMod": { + "Name": "AFAeroMod", + "Type": "Integer", + "Desc": "Type of blade airfoil aerodynamics model (switch) {1=steady model, 2=Beddoes-Leishman unsteady model} [AFAeroMod must be 1 when linearizing]", + "Line": 7, + "Value": 1, + "Size": false + }, + "TwrPotent": { + "Name": "TwrPotent", + "Type": "Integer", + "Desc": "Type tower influence on wind based on potential flow around the tower (switch) {0=none, 1=baseline potential flow, 2=potential flow with Bak correction}", + "Line": 8, + "Value": 0, + "Size": false + }, + "TwrShadow": { + "Name": "TwrShadow", + "Type": "Integer", + "Desc": "Calculate tower influence on wind based on downstream tower shadow (switch) {0=none, 1=Powles model, 2=Eames model}", + "Line": 9, + "Value": 0, + "Size": false + }, + "FrozenWake": { + "Name": "FrozenWake", + "Type": "Bool", + "Desc": "Assume frozen wake during linearization? (flag) [used only when WakeMod=1 and when linearizing]", + "Line": 11, + "Value": true + }, + "SkewMod": { + "Name": "SkewMod", + "Type": "Integer", + "Desc": "Type of skewed-wake correction model (switch) {1=uncoupled, 2=Pitt/Peters, 3=coupled} [unused when WakeMod=0 or 3]", + "Line": 23, + "Value": 0, + "Size": false + }, + "OLAFInputFileName": { + "Name": "OLAFInputFileName", + "Type": "Path", + "Desc": "Input file for OLAF [used only when WakeMod=3]", + "Line": 36, + "Value": "FileNotFound", + "FileType": "OLAF", + "Root": false + }, + "NumAFfiles": { + "Name": "NumAFfiles", + "Type": "Integer", + "Desc": "Number of airfoil files used (-)", + "Line": 47, + "Value": 8, + "Size": true + }, + "AFNames": { + "Name": "AFNames", + "Type": "Paths", + "Desc": "Airfoil file names (NumAFfiles lines) (quoted strings)", + "Line": 48, + "Value": [ + "Cylinder1.dat", + "Cylinder2.dat", + "DU40_A17.dat", + "DU35_A17.dat", + "DU30_A17.dat", + "DU25_A17.dat", + "DU21_A17.dat", + "NACA64_A17.dat" + ], + "FileType": "AirfoilInfo", + "Condensed": false + }, + "ADBlFile1": { + "Name": "ADBlFile(1)", + "Type": "Path", + "Desc": "Name of file containing distributed aerodynamic properties for Blade #1 (-)", + "Line": 58, + "Value": "NREL_5MW_AeroDyn_blade.dat", + "FileType": "Misc", + "Root": false + }, + "ADBlFile2": { + "Name": "ADBlFile(2)", + "Type": "Path", + "Desc": "Name of file containing distributed aerodynamic properties for Blade #2 (-) [unused if NumBl \u003c 2]", + "Line": 59, + "Value": "NREL_5MW_AeroDyn_blade.dat", + "FileType": "Misc", + "Root": false + }, + "ADBlFile3": { + "Name": "ADBlFile(3)", + "Type": "Path", + "Desc": "Name of file containing distributed aerodynamic properties for Blade #3 (-) [unused if NumBl \u003c 3]", + "Line": 60, + "Value": "NREL_5MW_AeroDyn_blade.dat", + "FileType": "Misc", + "Root": false + }, + "TFinFile": { + "Name": "TFinFile", + "Type": "Path", + "Desc": "Input file for tail fin aerodynamics [used only when TFinAero=True]", + "Line": 69, + "Value": "FileNotFound", + "FileType": "", + "Root": false + } + } + ], + "AeroDyn14": [], + "HydroDyn": [ + { + "Name": "NREL_5MW_Monopile_HydroDyn.dat", + "Type": "HydroDyn", + "Lines": [ + "------- HydroDyn v2.03.* Input File --------------------------------------------", + "NREL 5.0 MW offshore baseline floating platform input properties for the OC3 Monopile.", + "False Echo - Echo the input file data (flag)", + "---------------------- ENVIRONMENTAL CONDITIONS --------------------------------", + " \"default\" WtrDens - Water density (kg/m^3)", + " \"default\" WtrDpth - Water depth (meters)", + " \"default\" MSL2SWL - Offset between still-water level and mean sea level (meters) [positive upward; unused when WaveMod = 6; must be zero if PotMod=1 or 2]", + "---------------------- WAVES ---------------------------------------------------", + " 2 WaveMod - Incident wave kinematics model {0: none=still water, 1: regular (periodic), 1P#: regular with user-specified phase, 2: JONSWAP/Pierson-Moskowitz spectrum (irregular), 3: White noise spectrum (irregular), 4: user-defined spectrum from routine UserWaveSpctrm (irregular), 5: Externally generated wave-elevation time series, 6: Externally generated full wave-kinematics time series [option 6 is invalid for PotMod/=0]} (switch)", + " 0 WaveStMod - Model for stretching incident wave kinematics to instantaneous free surface {0: none=no stretching, 1: vertical stretching, 2: extrapolation stretching, 3: Wheeler stretching} (switch) [unused when WaveMod=0 or when PotMod/=0]", + " 3630 WaveTMax - Analysis time for incident wave calculations (sec) [unused when WaveMod=0; determines WaveDOmega=2Pi/WaveTMax in the IFFT]", + " 0.25 WaveDT - Time step for incident wave calculations (sec) [unused when WaveMod=0; 0.1\u003c=WaveDT\u003c=1.0 recommended; determines WaveOmegaMax=Pi/WaveDT in the IFFT]", + " 6 WaveHs - Significant wave height of incident waves (meters) [used only when WaveMod=1, 2, or 3]", + " 10 WaveTp - Peak-spectral period of incident waves (sec) [used only when WaveMod=1 or 2]", + "\"DEFAULT\" WavePkShp - Peak-shape parameter of incident wave spectrum (-) or DEFAULT (string) [used only when WaveMod=2; use 1.0 for Pierson-Moskowitz]", + " 0.15708 WvLowCOff - Low cut-off frequency or lower frequency limit of the wave spectrum beyond which the wave spectrum is zeroed (rad/s) [unused when WaveMod=0, 1, or 6]", + " 3.2 WvHiCOff - High cut-off frequency or upper frequency limit of the wave spectrum beyond which the wave spectrum is zeroed (rad/s) [unused when WaveMod=0, 1, or 6]", + " 0 WaveDir - Incident wave propagation heading direction (degrees) [unused when WaveMod=0 or 6]", + " 0 WaveDirMod - Directional spreading function {0: none, 1: COS2S} (-) [only used when WaveMod=2,3, or 4]", + " 1 WaveDirSpread - Wave direction spreading coefficient ( \u003e 0 ) (-) [only used when WaveMod=2,3, or 4 and WaveDirMod=1]", + " 1 WaveNDir - Number of wave directions (-) [only used when WaveMod=2,3, or 4 and WaveDirMod=1; odd number only]", + " 90 WaveDirRange - Range of wave directions (full range: WaveDir +/- 1/2*WaveDirRange) (degrees) [only used when WaveMod=2,3,or 4 and WaveDirMod=1]", + " 123456789 WaveSeed(1) - First random seed of incident waves [-2147483648 to 2147483647] (-) [unused when WaveMod=0, 5, or 6]", + " RANLUX WaveSeed(2) - Second random seed of incident waves [-2147483648 to 2147483647] for intrinsic pRNG, or an alternative pRNG: \"RanLux\" (-) [unused when WaveMod=0, 5, or 6]", + "TRUE WaveNDAmp - Flag for normally distributed amplitudes (flag) [only used when WaveMod=2, 3, or 4]", + "\"\" WvKinFile - Root name of externally generated wave data file(s) (quoted string) [used only when WaveMod=5 or 6]", + " 1 NWaveElev - Number of points where the incident wave elevations can be computed (-) [maximum of 9 output locations]", + " 0 WaveElevxi - List of xi-coordinates for points where the incident wave elevations can be output (meters) [NWaveElev points, separated by commas or white space; usused if NWaveElev = 0]", + " 0 WaveElevyi - List of yi-coordinates for points where the incident wave elevations can be output (meters) [NWaveElev points, separated by commas or white space; usused if NWaveElev = 0]", + "---------------------- 2ND-ORDER WAVES ----------------------------------------- [unused with WaveMod=0 or 6]", + "True WvDiffQTF - Full difference-frequency 2nd-order wave kinematics (flag)", + "True WvSumQTF - Full summation-frequency 2nd-order wave kinematics (flag)", + " 0 WvLowCOffD - Low frequency cutoff used in the difference-frequencies (rad/s) [Only used with a difference-frequency method]", + " 3.04292 WvHiCOffD - High frequency cutoff used in the difference-frequencies (rad/s) [Only used with a difference-frequency method]", + " 0.314159 WvLowCOffS - Low frequency cutoff used in the summation-frequencies (rad/s) [Only used with a summation-frequency method]", + " 3.2 WvHiCOffS - High frequency cutoff used in the summation-frequencies (rad/s) [Only used with a summation-frequency method]", + "---------------------- CURRENT ------------------------------------------------- [unused with WaveMod=6]", + " 0 CurrMod - Current profile model {0: none=no current, 1: standard, 2: user-defined from routine UserCurrent} (switch)", + " 0 CurrSSV0 - Sub-surface current velocity at still water level (m/s) [used only when CurrMod=1]", + "\"DEFAULT\" CurrSSDir - Sub-surface current heading direction (degrees) or DEFAULT (string) [used only when CurrMod=1]", + " 20 CurrNSRef - Near-surface current reference depth (meters) [used only when CurrMod=1]", + " 0 CurrNSV0 - Near-surface current velocity at still water level (m/s) [used only when CurrMod=1]", + " 0 CurrNSDir - Near-surface current heading direction (degrees) [used only when CurrMod=1]", + " 0 CurrDIV - Depth-independent current velocity (m/s) [used only when CurrMod=1]", + " 0 CurrDIDir - Depth-independent current heading direction (degrees) [used only when CurrMod=1]", + "---------------------- FLOATING PLATFORM --------------------------------------- [unused with WaveMod=6]", + " 0 PotMod - Potential-flow model {0: none=no potential flow, 1: frequency-to-time-domain transforms based on WAMIT output, 2: fluid-impulse theory (FIT)} (switch)", + " 1 ExctnMod - Wave-excitation model {0: no wave-excitation calculation, 1: DFT, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ssexctn INPUT FILE]", + " 0 RdtnMod - Radiation memory-effect model {0: no memory-effect calculation, 1: convolution, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ss INPUT FILE]", + " 60 RdtnTMax - Analysis time for wave radiation kernel calculations (sec) [only used when PotMod=1 and RdtnMod\u003e0; determines RdtnDOmega=Pi/RdtnTMax in the cosine transform; MAKE SURE THIS IS LONG ENOUGH FOR THE RADIATION IMPULSE RESPONSE FUNCTIONS TO DECAY TO NEAR-ZERO FOR THE GIVEN PLATFORM!]", + " 0.0125 RdtnDT - Time step for wave radiation kernel calculations (sec) [only used when PotMod=1 and ExctnMod\u003e0 or RdtnMod\u003e0; DT\u003c=RdtnDT\u003c=0.1 recommended; determines RdtnOmegaMax=Pi/RdtnDT in the cosine transform]", + " 1 NBody - Number of WAMIT bodies to be used (-) [\u003e=1; only used when PotMod=1. If NBodyMod=1, the WAMIT data contains a vector of size 6*NBody x 1 and matrices of size 6*NBody x 6*NBody; if NBodyMod\u003e1, there are NBody sets of WAMIT data each with a vector of size 6 x 1 and matrices of size 6 x 6]", + " 1 NBodyMod - Body coupling model {1: include coupling terms between each body and NBody in HydroDyn equals NBODY in WAMIT, 2: neglect coupling terms between each body and NBODY=1 with XBODY=0 in WAMIT, 3: Neglect coupling terms between each body and NBODY=1 with XBODY=/0 in WAMIT} (switch) [only used when PotMod=1]", + "\"unused\" PotFile - Root name of potential-flow model data; WAMIT output files containing the linear, nondimensionalized, hydrostatic restoring matrix (.hst), frequency-dependent hydrodynamic added mass matrix and damping matrix (.1), and frequency- and direction-dependent wave excitation force vector per unit wave amplitude (.3) (quoted string) [1 to NBody if NBodyMod\u003e1] [MAKE SURE THE FREQUENCIES INHERENT IN THESE WAMIT FILES SPAN THE PHYSICALLY-SIGNIFICANT RANGE OF FREQUENCIES FOR THE GIVEN PLATFORM; THEY MUST CONTAIN THE ZERO- AND INFINITE-FREQUENCY LIMITS!]", + " 1 WAMITULEN - Characteristic body length scale used to redimensionalize WAMIT output (meters) [1 to NBody if NBodyMod\u003e1] [only used when PotMod=1]", + " 0.0 PtfmRefxt - The xt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1]", + " 0.0 PtfmRefyt - The yt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1]", + " 0.0 PtfmRefzt - The zt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1. If NBodyMod=2,PtfmRefzt=0.0]", + " 0.0 PtfmRefztRot - The rotation about zt of the body reference frame(s) from xt/yt (degrees) [1 to NBody] [only used when PotMod=1]", + " 0 PtfmVol0 - Displaced volume of water when the body is in its undisplaced position (m^3) [1 to NBody] [only used when PotMod=1; USE THE SAME VALUE COMPUTED BY WAMIT AS OUTPUT IN THE .OUT FILE!]", + " 0.0 PtfmCOBxt - The xt offset of the center of buoyancy (COB) from (0,0) (meters) [1 to NBody] [only used when PotMod=1]", + " 0.0 PtfmCOByt - The yt offset of the center of buoyancy (COB) from (0,0) (meters) [1 to NBody] [only used when PotMod=1]", + "---------------------- 2ND-ORDER FLOATING PLATFORM FORCES ---------------------- [unused with WaveMod=0 or 6, or PotMod=0 or 2]", + " 0 MnDrift - Mean-drift 2nd-order forces computed {0: None; [7, 8, 9, 10, 11, or 12]: WAMIT file to use} [Only one of MnDrift, NewmanApp, or DiffQTF can be non-zero. If NBody\u003e1, MnDrift /=8]", + " 0 NewmanApp - Mean- and slow-drift 2nd-order forces computed with Newman's approximation {0: None; [7, 8, 9, 10, 11, or 12]: WAMIT file to use} [Only one of MnDrift, NewmanApp, or DiffQTF can be non-zero. If NBody\u003e1, NewmanApp/=8. Used only when WaveDirMod=0]", + " 0 DiffQTF - Full difference-frequency 2nd-order forces computed with full QTF {0: None; [10, 11, or 12]: WAMIT file to use} [Only one of MnDrift, NewmanApp, or DiffQTF can be non-zero]", + " 0 SumQTF - Full summation -frequency 2nd-order forces computed with full QTF {0: None; [10, 11, or 12]: WAMIT file to use}", + "---------------------- PLATFORM ADDITIONAL STIFFNESS AND DAMPING -------------- [unused with PotMod=0 or 2]", + " 0 AddF0 - Additional preload (N, N-m) [If NBodyMod=1, one size 6*NBody x 1 vector; if NBodyMod\u003e1, NBody size 6 x 1 vectors]", + " 0", + " 0", + " 0", + " 0", + " 0", + " 0 0 0 0 0 0 AddCLin - Additional linear stiffness (N/m, N/rad, N-m/m, N-m/rad) [If NBodyMod=1, one size 6*NBody x 6*NBody matrix; if NBodyMod\u003e1, NBody size 6 x 6 matrices]", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0 AddBLin - Additional linear damping(N/(m/s), N/(rad/s), N-m/(m/s), N-m/(rad/s)) [If NBodyMod=1, one size 6*NBody x 6*NBody matrix; if NBodyMod\u003e1, NBody size 6 x 6 matrices]", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0 AddBQuad - Additional quadratic drag(N/(m/s)^2, N/(rad/s)^2, N-m(m/s)^2, N-m/(rad/s)^2) [If NBodyMod=1, one size 6*NBody x 6*NBody matrix; if NBodyMod\u003e1, NBody size 6 x 6 matrices]", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + " 0 0 0 0 0 0", + "---------------------- AXIAL COEFFICIENTS --------------------------------------", + " 1 NAxCoef - Number of axial coefficients (-)", + "AxCoefID AxCd AxCa AxCp", + " (-) (-) (-) (-)", + " 1 0.00 0.00 1.00", + "---------------------- MEMBER JOINTS -------------------------------------------", + " 2 NJoints - Number of joints (-) [must be exactly 0 or at least 2]", + "JointID Jointxi Jointyi Jointzi JointAxID JointOvrlp [JointOvrlp= 0: do nothing at joint, 1: eliminate overlaps by calculating super member]", + " (-) (m) (m) (m) (-) (switch)", + " 1 0.00000 0.00000 -20.00010 1 0", + " 2 0.00000 0.00000 10.00000 1 0", + "---------------------- MEMBER CROSS-SECTION PROPERTIES -------------------------", + " 1 NPropSets - Number of member property sets (-)", + "PropSetID PropD PropThck", + " (-) (m) (m)", + " 1 6.00000 0.06000", + "---------------------- SIMPLE HYDRODYNAMIC COEFFICIENTS (model 1) --------------", + " SimplCd SimplCdMG SimplCa SimplCaMG SimplCp SimplCpMG SimplAxCd SimplAxCdMG SimplAxCa SimplAxCaMG SimplAxCp SimplAxCpMG", + " (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-)", + " 1.00 1.00 1.00 1.00 1.00 1.00 1.00 0.00 0.00 1.00 1.00 1.00 ", + "---------------------- DEPTH-BASED HYDRODYNAMIC COEFFICIENTS (model 2) ---------", + " 0 NCoefDpth - Number of depth-dependent coefficients (-)", + "Dpth DpthCd DpthCdMG DpthCa DpthCaMG DpthCp DpthCpMG DpthAxCd DpthAxCdMG DpthAxCa DpthAxCaMG DpthAxCp DpthAxCpMG", + "(m) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-)", + "---------------------- MEMBER-BASED HYDRODYNAMIC COEFFICIENTS (model 3) --------", + " 0 NCoefMembers - Number of member-based coefficients (-)", + "MemberID MemberCd1 MemberCd2 MemberCdMG1 MemberCdMG2 MemberCa1 MemberCa2 MemberCaMG1 MemberCaMG2 MemberCp1 MemberCp2 MemberCpMG1 MemberCpMG2 MemberAxCd1 MemberAxCd2 MemberAxCdMG1 MemberAxCdMG2 MemberAxCa1 MemberAxCa2 MemberAxCaMG1 MemberAxCaMG2 MemberAxCp1 MemberAxCp2 MemberAxCpMG1 MemberAxCpMG2", + " (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-)", + "-------------------- MEMBERS -------------------------------------------------", + " 1 NMembers - Number of members (-)", + "MemberID MJointID1 MJointID2 MPropSetID1 MPropSetID2 MDivSize MCoefMod PropPot [MCoefMod=1: use simple coeff table, 2: use depth-based coeff table, 3: use member-based coeff table] [ PropPot/=0 if member is modeled with potential-flow theory]", + " (-) (-) (-) (-) (-) (m) (switch) (flag)", + " 1 1 2 1 1 0.5000 1 FALSE", + "---------------------- FILLED MEMBERS ------------------------------------------", + " 0 NFillGroups - Number of filled member groups (-) [If FillDens = DEFAULT, then FillDens = WtrDens; FillFSLoc is related to MSL2SWL]", + "FillNumM FillMList FillFSLoc FillDens", + "(-) (-) (m) (kg/m^3)", + "---------------------- MARINE GROWTH -------------------------------------------", + " 0 NMGDepths - Number of marine-growth depths specified (-)", + "MGDpth MGThck MGDens", + "(m) (m) (kg/m^3)", + "---------------------- MEMBER OUTPUT LIST --------------------------------------", + " 0 NMOutputs - Number of member outputs (-) [must be \u003c= 99]", + "MemberID NOutLoc NodeLocs [NOutLoc \u003c 10; node locations are normalized distance from the start of the member, and must be \u003e=0 and \u003c= 1] [unused if NMOutputs=0]", + " (-) (-) (-)", + "---------------------- JOINT OUTPUT LIST ---------------------------------------", + " 0 NJOutputs - Number of joint outputs [Must be \u003c 10]", + " 0 JOutLst - List of JointIDs which are to be output (-)[unused if NJOutputs=0]", + "---------------------- OUTPUT --------------------------------------------------", + "True HDSum - Output a summary file [flag]", + "False OutAll - Output all user-specified member and joint loads (only at each member end, not interior locations) [flag]", + " 2 OutSwtch - Output requested channels to: [1=Hydrodyn.out, 2=GlueCode.out, 3=both files]", + "\"ES11.4e2\" OutFmt - Output format for numerical results (quoted string) [not checked for validity!]", + "\"A11\" OutSFmt - Output format for header strings (quoted string) [not checked for validity!]", + "---------------------- OUTPUT CHANNELS -----------------------------------------", + "\"Wave1Elev\" - Wave elevation at the WAMIT reference point (0,0)", + "\"HydroFxi, HydroFyi, HydroFzi\"", + "\"HydroMxi, HydroMyi, HydroMzi\"", + "END of output channels and end of file. (the word \"END\" must appear in the first 3 columns of this line)" + ], + "WaveMod": { + "Name": "WaveMod", + "Type": "Integer", + "Desc": "Incident wave kinematics model {0: none=still water, 1: regular (periodic), 1P#: regular with user-specified phase, 2: JONSWAP/Pierson-Moskowitz spectrum (irregular), 3: White noise spectrum (irregular), 4: user-defined spectrum from routine UserWaveSpctrm (irregular), 5: Externally generated wave-elevation time series, 6: Externally generated full wave-kinematics time series [option 6 is invalid for PotMod/=0]} (switch)", + "Line": 9, + "Value": 0, + "Size": false + }, + "WvDiffQTF": { + "Name": "WvDiffQTF", + "Type": "Bool", + "Desc": "Full difference-frequency 2nd-order wave kinematics (flag)", + "Line": 31, + "Value": false + }, + "WvSumQTF": { + "Name": "WvSumQTF", + "Type": "Bool", + "Desc": "Full summation-frequency 2nd-order wave kinematics (flag)", + "Line": 32, + "Value": false + }, + "ExctnMod": { + "Name": "ExctnMod", + "Type": "Integer", + "Desc": "Wave-excitation model {0: no wave-excitation calculation, 1: DFT, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ssexctn INPUT FILE]", + "Line": 48, + "Value": 0, + "Size": false + }, + "PotFile": { + "Name": "PotFile", + "Type": "Path", + "Desc": "Root name of potential-flow model data; WAMIT output files containing the linear, nondimensionalized, hydrostatic restoring matrix (.hst), frequency-dependent hydrodynamic added mass matrix and damping matrix (.1), and frequency- and direction-dependent wave excitation force vector per unit wave amplitude (.3) (quoted string) [1 to NBody if NBodyMod\u003e1] [MAKE SURE THE FREQUENCIES INHERENT IN THESE WAMIT FILES SPAN THE PHYSICALLY-SIGNIFICANT RANGE OF FREQUENCIES FOR THE GIVEN PLATFORM; THEY MUST CONTAIN THE ZERO- AND INFINITE-FREQUENCY LIMITS!]", + "Line": 54, + "Value": "unused", + "FileType": "Misc", + "Root": true + } + } + ], + "ServoDyn": [ + { + "Name": "NREL_5MW_Monopile_ServoDyn.dat", + "Type": "ServoDyn", + "Lines": [ + "------- SERVODYN v1.05.* INPUT FILE --------------------------------------------", + "NREL 5.0 MW Baseline Wind Turbine for Use in Offshore Analysis. Properties from Dutch Offshore Wind Energy Converter (DOWEC) 6MW Pre-Design (10046_009.pdf) and REpower 5M 5MW (5m_uk.pdf);", + "---------------------- SIMULATION CONTROL --------------------------------------", + "False Echo - Echo input data to \u003cRootName\u003e.ech (flag)", + "\"default\" DT - Communication interval for controllers (s) (or \"default\")", + "---------------------- PITCH CONTROL -------------------------------------------", + " 5 PCMode - Pitch control mode {0: none, 3: user-defined from routine PitchCntrl, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + " 0 TPCOn - Time to enable active pitch control (s) [unused when PCMode=0]", + " 9999.9 TPitManS(1) - Time to start override pitch maneuver for blade 1 and end standard pitch control (s)", + " 9999.9 TPitManS(2) - Time to start override pitch maneuver for blade 2 and end standard pitch control (s)", + " 9999.9 TPitManS(3) - Time to start override pitch maneuver for blade 3 and end standard pitch control (s) [unused for 2 blades]", + " 2 PitManRat(1) - Pitch rate at which override pitch maneuver heads toward final pitch angle for blade 1 (deg/s)", + " 2 PitManRat(2) - Pitch rate at which override pitch maneuver heads toward final pitch angle for blade 2 (deg/s)", + " 2 PitManRat(3) - Pitch rate at which override pitch maneuver heads toward final pitch angle for blade 3 (deg/s) [unused for 2 blades]", + " 0 BlPitchF(1) - Blade 1 final pitch for pitch maneuvers (degrees)", + " 0 BlPitchF(2) - Blade 2 final pitch for pitch maneuvers (degrees)", + " 0 BlPitchF(3) - Blade 3 final pitch for pitch maneuvers (degrees) [unused for 2 blades]", + "---------------------- GENERATOR AND TORQUE CONTROL ----------------------------", + " 5 VSContrl - Variable-speed control mode {0: none, 1: simple VS, 3: user-defined from routine UserVSCont, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + " 2 GenModel - Generator model {1: simple, 2: Thevenin, 3: user-defined from routine UserGen} (switch) [used only when VSContrl=0]", + " 94.4 GenEff - Generator efficiency [ignored by the Thevenin and user-defined generator models] (%)", + "True GenTiStr - Method to start the generator {T: timed using TimGenOn, F: generator speed using SpdGenOn} (flag)", + "True GenTiStp - Method to stop the generator {T: timed using TimGenOf, F: when generator power = 0} (flag)", + " 9999.9 SpdGenOn - Generator speed to turn on the generator for a startup (HSS speed) (rpm) [used only when GenTiStr=False]", + " 0 TimGenOn - Time to turn on the generator for a startup (s) [used only when GenTiStr=True]", + " 9999.9 TimGenOf - Time to turn off the generator (s) [used only when GenTiStp=True]", + "---------------------- SIMPLE VARIABLE-SPEED TORQUE CONTROL --------------------", + " 9999.9 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1]", + " 9999.9 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1]", + " 9999.9 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1]", + " 9999.9 VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1]", + "---------------------- SIMPLE INDUCTION GENERATOR ------------------------------", + " 9999.9 SIG_SlPc - Rated generator slip percentage (%) [used only when VSContrl=0 and GenModel=1]", + " 9999.9 SIG_SySp - Synchronous (zero-torque) generator speed (rpm) [used only when VSContrl=0 and GenModel=1]", + " 9999.9 SIG_RtTq - Rated torque (N-m) [used only when VSContrl=0 and GenModel=1]", + " 9999.9 SIG_PORt - Pull-out ratio (Tpullout/Trated) (-) [used only when VSContrl=0 and GenModel=1]", + "---------------------- THEVENIN-EQUIVALENT INDUCTION GENERATOR -----------------", + " 9999.9 TEC_Freq - Line frequency [50 or 60] (Hz) [used only when VSContrl=0 and GenModel=2]", + " 9998 TEC_NPol - Number of poles [even integer \u003e 0] (-) [used only when VSContrl=0 and GenModel=2]", + " 9999.9 TEC_SRes - Stator resistance (ohms) [used only when VSContrl=0 and GenModel=2]", + " 9999.9 TEC_RRes - Rotor resistance (ohms) [used only when VSContrl=0 and GenModel=2]", + " 9999.9 TEC_VLL - Line-to-line RMS voltage (volts) [used only when VSContrl=0 and GenModel=2]", + " 9999.9 TEC_SLR - Stator leakage reactance (ohms) [used only when VSContrl=0 and GenModel=2]", + " 9999.9 TEC_RLR - Rotor leakage reactance (ohms) [used only when VSContrl=0 and GenModel=2]", + " 9999.9 TEC_MR - Magnetizing reactance (ohms) [used only when VSContrl=0 and GenModel=2]", + "---------------------- HIGH-SPEED SHAFT BRAKE ----------------------------------", + " 0 HSSBrMode - HSS brake model {0: none, 1: simple, 3: user-defined from routine UserHSSBr, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + " 9999.9 THSSBrDp - Time to initiate deployment of the HSS brake (s)", + " 0.6 HSSBrDT - Time for HSS-brake to reach full deployment once initiated (sec) [used only when HSSBrMode=1]", + " 28116.2 HSSBrTqF - Fully deployed HSS-brake torque (N-m)", + "---------------------- NACELLE-YAW CONTROL -------------------------------------", + " 0 YCMode - Yaw control mode {0: none, 3: user-defined from routine UserYawCont, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + " 9999.9 TYCOn - Time to enable active yaw control (s) [unused when YCMode=0]", + " 0 YawNeut - Neutral yaw position--yaw spring force is zero at this yaw (degrees)", + "9.02832E+09 YawSpr - Nacelle-yaw spring constant (N-m/rad)", + " 1.916E+07 YawDamp - Nacelle-yaw damping constant (N-m/(rad/s))", + " 9999.9 TYawManS - Time to start override yaw maneuver and end standard yaw control (s)", + " 2 YawManRat - Yaw maneuver rate (in absolute value) (deg/s)", + " 0 NacYawF - Final yaw angle for override yaw maneuvers (degrees)", + "---------------------- AERODYNAMIC FLOW CONTROL --------------------------------", + " 0 AfCmode - Airfoil control mode {0: none, 1: cosine wave cycle, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + " 0 AfC_Mean - Mean level for cosine cycling or steady value (-) [used only with AfCmode==1]", + " 0 AfC_Amp - Amplitude for for cosine cycling of flap signal (-) [used only with AfCmode==1]", + " 0 AfC_Phase - Phase relative to the blade azimuth (0 is vertical) for for cosine cycling of flap signal (deg) [used only with AfCmode==1]", + "---------------------- STRUCTURAL CONTROL --------------------------------------", + "0 NumBStC - Number of blade structural controllers (integer)", + "\"unused\" BStCfiles - Name of the files for blade structural controllers (quoted strings) [unused when NumBStC==0]", + "0 NumNStC - Number of nacelle structural controllers (integer)", + "\"unused\" NStCfiles - Name of the files for nacelle structural controllers (quoted strings) [unused when NumNStC==0]", + "0 NumTStC - Number of tower structural controllers (integer)", + "\"unused\" TStCfiles - Name of the files for tower structural controllers (quoted strings) [unused when NumTStC==0]", + "0 NumSStC - Number of substructure structural controllers (integer)", + "\"unused\" SStCfiles - Name of the files for substructure structural controllers (quoted strings) [unused when NumSStC==0]", + "---------------------- CABLE CONTROL -------------------------------------------", + " 0 CCmode - Cable control mode {0: none, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + "---------------------- BLADED INTERFACE ---------------------------------------- [used only with Bladed Interface]", + "\"../5MW_Baseline/ServoData/DISCON.dll\" DLL_FileName - Name/location of the dynamic library {.dll [Windows] or .so [Linux]} in the Bladed-DLL format (-) [used only with Bladed Interface]", + "\"DISCON.IN\" DLL_InFile - Name of input file sent to the DLL (-) [used only with Bladed Interface]", + "\"DISCON\" DLL_ProcName - Name of procedure in DLL to be called (-) [case sensitive; used only with DLL Interface]", + "\"default\" DLL_DT - Communication interval for dynamic library (s) (or \"default\") [used only with Bladed Interface]", + "false DLL_Ramp - Whether a linear ramp should be used between DLL_DT time steps [introduces time shift when true] (flag) [used only with Bladed Interface]", + " 9999.9 BPCutoff - Cutoff frequency for low-pass filter on blade pitch from DLL (Hz) [used only with Bladed Interface]", + " 0 NacYaw_North - Reference yaw angle of the nacelle when the upwind end points due North (deg) [used only with Bladed Interface]", + " 0 Ptch_Cntrl - Record 28: Use individual pitch control {0: collective pitch; 1: individual pitch control} (switch) [used only with Bladed Interface]", + " 0 Ptch_SetPnt - Record 5: Below-rated pitch angle set-point (deg) [used only with Bladed Interface]", + " 0 Ptch_Min - Record 6: Minimum pitch angle (deg) [used only with Bladed Interface]", + " 0 Ptch_Max - Record 7: Maximum pitch angle (deg) [used only with Bladed Interface]", + " 0 PtchRate_Min - Record 8: Minimum pitch rate (most negative value allowed) (deg/s) [used only with Bladed Interface]", + " 0 PtchRate_Max - Record 9: Maximum pitch rate (deg/s) [used only with Bladed Interface]", + " 0 Gain_OM - Record 16: Optimal mode gain (Nm/(rad/s)^2) [used only with Bladed Interface]", + " 0 GenSpd_MinOM - Record 17: Minimum generator speed (rpm) [used only with Bladed Interface]", + " 0 GenSpd_MaxOM - Record 18: Optimal mode maximum speed (rpm) [used only with Bladed Interface]", + " 0 GenSpd_Dem - Record 19: Demanded generator speed above rated (rpm) [used only with Bladed Interface]", + " 0 GenTrq_Dem - Record 22: Demanded generator torque above rated (Nm) [used only with Bladed Interface]", + " 0 GenPwr_Dem - Record 13: Demanded power (W) [used only with Bladed Interface]", + "---------------------- BLADED INTERFACE TORQUE-SPEED LOOK-UP TABLE -------------", + " 0 DLL_NumTrq - Record 26: No. of points in torque-speed look-up table {0 = none and use the optimal mode parameters; nonzero = ignore the optimal mode PARAMETERs by setting Record 16 to 0.0} (-) [used only with Bladed Interface]", + " GenSpd_TLU GenTrq_TLU", + " (rpm) (Nm)", + "---------------------- OUTPUT --------------------------------------------------", + "True SumPrint - Print summary data to \u003cRootName\u003e.sum (flag) (currently unused)", + " 1 OutFile - Switch to determine where output will be placed: {1: in module output file only; 2: in glue code output file only; 3: both} (currently unused)", + "True TabDelim - Use tab delimiters in text tabular output file? (flag) (currently unused)", + "\"ES10.3E2\" OutFmt - Format used for text tabular output (except time). Resulting field should be 10 characters. (quoted string) (currently unused)", + " 30 TStart - Time to begin tabular output (s) (currently unused)", + " OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-)", + "\"GenPwr\" - Electrical generator power and torque", + "\"GenTq\" - Electrical generator power and torque", + "END of input file (the word \"END\" must appear in the first 3 columns of this last OutList line)", + "---------------------------------------------------------------------------------------" + ], + "PCMode": { + "Name": "PCMode", + "Type": "Integer", + "Desc": "Pitch control mode {0: none, 3: user-defined from routine PitchCntrl, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + "Line": 7, + "Value": 5, + "Size": false + }, + "VSContrl": { + "Name": "VSContrl", + "Type": "Integer", + "Desc": "Variable-speed control mode {0: none, 1: simple VS, 3: user-defined from routine UserVSCont, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + "Line": 19, + "Value": 5, + "Size": false + }, + "VS_RtGnSp": { + "Name": "VS_RtGnSp", + "Type": "Real", + "Desc": "Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1]", + "Line": 28, + "Value": 9999.9 + }, + "VS_RtTq": { + "Name": "VS_RtTq", + "Type": "Real", + "Desc": "Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1]", + "Line": 29, + "Value": 9999.9 + }, + "VS_Rgn2K": { + "Name": "VS_Rgn2K", + "Type": "Real", + "Desc": "Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1]", + "Line": 30, + "Value": 9999.9 + }, + "VS_SlPc": { + "Name": "VS_SlPc", + "Type": "Real", + "Desc": "Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1]", + "Line": 31, + "Value": 9999.9 + }, + "HSSBrMode": { + "Name": "HSSBrMode", + "Type": "Integer", + "Desc": "HSS brake model {0: none, 1: simple, 3: user-defined from routine UserHSSBr, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + "Line": 47, + "Value": 0, + "Size": false + }, + "YCMode": { + "Name": "YCMode", + "Type": "Integer", + "Desc": "Yaw control mode {0: none, 3: user-defined from routine UserYawCont, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch)", + "Line": 52, + "Value": 0, + "Size": false + }, + "NumBStC": { + "Name": "NumBStC", + "Type": "Integer", + "Desc": "Number of blade structural controllers (integer)", + "Line": 66, + "Value": 0, + "Size": true + }, + "BStCfiles": { + "Name": "BStCfiles", + "Type": "Paths", + "Desc": "Name of the files for blade structural controllers (quoted strings) [unused when NumBStC==0]", + "Line": 67, + "Value": null, + "FileType": "StControl", + "Condensed": true + }, + "NumNStC": { + "Name": "NumNStC", + "Type": "Integer", + "Desc": "Number of nacelle structural controllers (integer)", + "Line": 68, + "Value": 0, + "Size": true + }, + "NStCfiles": { + "Name": "NStCfiles", + "Type": "Paths", + "Desc": "Name of the files for nacelle structural controllers (quoted strings) [unused when NumNStC==0]", + "Line": 69, + "Value": null, + "FileType": "StControl", + "Condensed": true + }, + "NumTStC": { + "Name": "NumTStC", + "Type": "Integer", + "Desc": "Number of tower structural controllers (integer)", + "Line": 70, + "Value": 0, + "Size": true + }, + "TStCfiles": { + "Name": "TStCfiles", + "Type": "Paths", + "Desc": "Name of the files for tower structural controllers (quoted strings) [unused when NumTStC==0]", + "Line": 71, + "Value": null, + "FileType": "StControl", + "Condensed": true + }, + "NumSStC": { + "Name": "NumSStC", + "Type": "Integer", + "Desc": "Number of substructure structural controllers (integer)", + "Line": 72, + "Value": 0, + "Size": true + }, + "SStCfiles": { + "Name": "SStCfiles", + "Type": "Paths", + "Desc": "Name of the files for substructure structural controllers (quoted strings) [unused when NumSStC==0]", + "Line": 73, + "Value": null, + "FileType": "StControl", + "Condensed": true + } + } + ], + "InflowWind": [ + { + "Name": "NREL_5MW_InflowWind.dat", + "Type": "InflowWind", + "Lines": [ + "------- InflowWind v3.01.* INPUT FILE -------------------------------------------------------------------------", + "13 m/s Steady Wind", + "---------------------------------------------------------------------------------------------------------------", + " False Echo - Echo input data to \u003cRootName\u003e.ech (flag)", + " 1 WindType - switch for wind file type (1=steady; 2=uniform; 3=binary TurbSim FF; 4=binary Bladed-style FF; 5=HAWC format; 6=User defined; 7=native Bladed FF)", + " 0 PropagationDir - Direction of wind propagation (meteorological rotation from aligned with X (positive rotates towards -Y) -- degrees) (not used for native Bladed format WindType=7)", + " 0 VFlowAng - Upflow angle (degrees) (not used for native Bladed format WindType=7)", + " False VelInterpCubic - Use cubic interpolation for velocity in time (false=linear, true=cubic) [Used with WindType=2,3,4,5,7]", + " 1 NWindVel - Number of points to output the wind velocity (0 to 9)", + " 0 WindVxiList - List of coordinates in the inertial X direction (m)", + " 0 WindVyiList - List of coordinates in the inertial Y direction (m)", + " 90 WindVziList - List of coordinates in the inertial Z direction (m)", + "================== Parameters for Steady Wind Conditions [used only for WindType = 1] =========================", + " 13 HWindSpeed - Horizontal wind speed (m/s)", + " 90 RefHt - Reference height for horizontal wind speed (m)", + " 0.2 PLExp - Power law exponent (-)", + "================== Parameters for Uniform wind file [used only for WindType = 2] ============================", + "\"unused\" Filename_Uni - Filename of time series data for uniform wind field. (-)", + " 90 RefHt_Uni - Reference height for horizontal wind speed (m)", + " 125.88 RefLength - Reference length for linear horizontal and vertical sheer (-)", + "================== Parameters for Binary TurbSim Full-Field files [used only for WindType = 3] ==============", + "\"unused\" FileName_BTS - Name of the Full field wind file to use (.bts)", + "================== Parameters for Binary Bladed-style Full-Field files [used only for WindType = 4 or WindType = 7] =========", + "\"unused\" FileNameRoot - WindType=4: Rootname of the full-field wind file to use (.wnd, .sum); WindType=7: name of the intermediate file with wind scaling values", + "False TowerFile - Have tower file (.twr) (flag) ignored when WindType = 7", + "================== Parameters for HAWC-format binary files [Only used with WindType = 5] =====================", + "\"unused\" FileName_u - name of the file containing the u-component fluctuating wind (.bin)", + "\"unused\" FileName_v - name of the file containing the v-component fluctuating wind (.bin)", + "\"unused\" FileName_w - name of the file containing the w-component fluctuating wind (.bin)", + " 64 nx - number of grids in the x direction (in the 3 files above) (-)", + " 32 ny - number of grids in the y direction (in the 3 files above) (-)", + " 32 nz - number of grids in the z direction (in the 3 files above) (-)", + " 16 dx - distance (in meters) between points in the x direction (m)", + " 3 dy - distance (in meters) between points in the y direction (m)", + " 3 dz - distance (in meters) between points in the z direction (m)", + " 90 RefHt_Hawc - reference height; the height (in meters) of the vertical center of the grid (m)", + " ------------- Scaling parameters for turbulence ---------------------------------------------------------", + " 1 ScaleMethod - Turbulence scaling method [0 = none, 1 = direct scaling, 2 = calculate scaling factor based on a desired standard deviation]", + " 1 SFx - Turbulence scaling factor for the x direction (-) [ScaleMethod=1]", + " 1 SFy - Turbulence scaling factor for the y direction (-) [ScaleMethod=1]", + " 1 SFz - Turbulence scaling factor for the z direction (-) [ScaleMethod=1]", + " 12 SigmaFx - Turbulence standard deviation to calculate scaling from in x direction (m/s) [ScaleMethod=2]", + " 8 SigmaFy - Turbulence standard deviation to calculate scaling from in y direction (m/s) [ScaleMethod=2]", + " 2 SigmaFz - Turbulence standard deviation to calculate scaling from in z direction (m/s) [ScaleMethod=2]", + " ------------- Mean wind profile parameters (added to HAWC-format files) ---------------------------------", + " 5 URef - Mean u-component wind speed at the reference height (m/s)", + " 2 WindProfile - Wind profile type (0=constant;1=logarithmic,2=power law)", + " 0 PLExp_Hawc - Power law exponent (-) (used for PL wind profile type only)", + " 0.03 Z0 - Surface roughness length (m) (used for LG wind profile type only)", + " 0 XOffset - Initial offset in +x direction (shift of wind box)", + "================== LIDAR Parameters ===========================================================================", + " 0 SensorType - Switch for lidar configuration (0 = None, 1 = Single Point Beam(s), 2 = Continuous, 3 = Pulsed)", + " 0 NumPulseGate - Number of lidar measurement gates (used when SensorType = 3)", + " 30 PulseSpacing - Distance between range gates (m) (used when SensorType = 3)", + " 0 NumBeam - Number of lidar measurement beams (0-5)(used when SensorType = 1)", + " -200 FocalDistanceX - Focal distance co-ordinates of the lidar beam in the x direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m)", + " 0 FocalDistanceY - Focal distance co-ordinates of the lidar beam in the y direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m)", + " 0 FocalDistanceZ - Focal distance co-ordinates of the lidar beam in the z direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m)", + "0.0 0.0 0.0 RotorApexOffsetPos - Offset of the lidar from hub height (m)", + " 17 URefLid - Reference average wind speed for the lidar[m/s]", + " 0.25 MeasurementInterval - Time between each measurement [s]", + " False LidRadialVel - TRUE =\u003e return radial component, FALSE =\u003e return 'x' direction estimate", + " 1 ConsiderHubMotion - Flag whether to consider the hub motion's impact on Lidar measurements", + "====================== OUTPUT ==================================================", + "False SumPrint - Print summary data to \u003cRootName\u003e.IfW.sum (flag)", + " OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-)", + "\"Wind1VelX\" X-direction wind velocity at point WindList(1)", + "\"Wind1VelY\" Y-direction wind velocity at point WindList(1)", + "\"Wind1VelZ\" Z-direction wind velocity at point WindList(1)", + "END of input file (the word \"END\" must appear in the first 3 columns of this last OutList line)", + "---------------------------------------------------------------------------------------" + ], + "WindType": { + "Name": "WindType", + "Type": "Integer", + "Desc": "switch for wind file type (1=steady; 2=uniform; 3=binary TurbSim FF; 4=binary Bladed-style FF; 5=HAWC format; 6=User defined; 7=native Bladed FF)", + "Line": 5, + "Value": 1, + "Size": false + }, + "PropagationDir": { + "Name": "PropagationDir", + "Type": "Real", + "Desc": "Direction of wind propagation (meteorological rotation from aligned with X (positive rotates towards -Y) -- degrees) (not used for native Bladed format WindType=7)", + "Line": 6, + "Value": 0 + }, + "VFlowAng": { + "Name": "VFlowAng", + "Type": "Real", + "Desc": "Upflow angle (degrees) (not used for native Bladed format WindType=7)", + "Line": 7, + "Value": 0 + }, + "HWindSpeed": { + "Name": "HWindSpeed", + "Type": "Real", + "Desc": "Horizontal wind speed (m/s)", + "Line": 14, + "Value": 13 + }, + "PLExp": { + "Name": "PLExp", + "Type": "Real", + "Desc": "Power law exponent (-)", + "Line": 16, + "Value": 0.2 + } + } + ], + "OLAF": [], + "Misc": [ + { + "Name": "NREL_5MW_ElastoDyn_Blade.dat", + "Type": "Misc", + "Lines": [ + "------- ELASTODYN V1.00.* INDIVIDUAL BLADE INPUT FILE --------------------------", + "NREL 5.0 MW offshore baseline blade input properties.", + "---------------------- BLADE PARAMETERS ----------------------------------------", + " 49 NBlInpSt - Number of blade input stations (-)", + " 0.477465 BldFlDmp(1) - Blade flap mode #1 structural damping in percent of critical (%)", + " 0.477465 BldFlDmp(2) - Blade flap mode #2 structural damping in percent of critical (%)", + " 0.477465 BldEdDmp(1) - Blade edge mode #1 structural damping in percent of critical (%)", + "---------------------- BLADE ADJUSTMENT FACTORS --------------------------------", + " 1 FlStTunr(1) - Blade flapwise modal stiffness tuner, 1st mode (-)", + " 1 FlStTunr(2) - Blade flapwise modal stiffness tuner, 2nd mode (-)", + " 1.04536 AdjBlMs - Factor to adjust blade mass density (-) !bjj: value for AD14=1.04536; value for AD15=1.057344 (it would be nice to enter the requested blade mass instead of a factor here)", + " 1 AdjFlSt - Factor to adjust blade flap stiffness (-)", + " 1 AdjEdSt - Factor to adjust blade edge stiffness (-)", + "---------------------- DISTRIBUTED BLADE PROPERTIES ----------------------------", + " BlFract PitchAxis StrcTwst BMassDen FlpStff EdgStff", + " (-) (-) (deg) (kg/m) (Nm^2) (Nm^2)", + "0.0000000E+00 2.5000000E-01 1.3308000E+01 6.7893500E+02 1.8110000E+10 1.8113600E+10", + "3.2500000E-03 2.5000000E-01 1.3308000E+01 6.7893500E+02 1.8110000E+10 1.8113600E+10", + "1.9510000E-02 2.5049000E-01 1.3308000E+01 7.7336300E+02 1.9424900E+10 1.9558600E+10", + "3.5770000E-02 2.5490000E-01 1.3308000E+01 7.4055000E+02 1.7455900E+10 1.9497800E+10", + "5.2030000E-02 2.6716000E-01 1.3308000E+01 7.4004200E+02 1.5287400E+10 1.9788800E+10", + "6.8290000E-02 2.7941000E-01 1.3308000E+01 5.9249600E+02 1.0782400E+10 1.4858500E+10", + "8.4550000E-02 2.9167000E-01 1.3308000E+01 4.5027500E+02 7.2297200E+09 1.0220600E+10", + "1.0081000E-01 3.0392000E-01 1.3308000E+01 4.2405400E+02 6.3095400E+09 9.1447000E+09", + "1.1707000E-01 3.1618000E-01 1.3308000E+01 4.0063800E+02 5.5283600E+09 8.0631600E+09", + "1.3335000E-01 3.2844000E-01 1.3308000E+01 3.8206200E+02 4.9800600E+09 6.8844400E+09", + "1.4959000E-01 3.4069000E-01 1.3308000E+01 3.9965500E+02 4.9368400E+09 7.0091800E+09", + "1.6585000E-01 3.5294000E-01 1.3308000E+01 4.2632100E+02 4.6916600E+09 7.1676800E+09", + "1.8211000E-01 3.6519000E-01 1.3181000E+01 4.1682000E+02 3.9494600E+09 7.2716600E+09", + "1.9837000E-01 3.7500000E-01 1.2848000E+01 4.0618600E+02 3.3865200E+09 7.0817000E+09", + "2.1465000E-01 3.7500000E-01 1.2192000E+01 3.8142000E+02 2.9337400E+09 6.2445300E+09", + "2.3089000E-01 3.7500000E-01 1.1561000E+01 3.5282200E+02 2.5689600E+09 5.0489600E+09", + "2.4715000E-01 3.7500000E-01 1.1072000E+01 3.4947700E+02 2.3886500E+09 4.9484900E+09", + "2.6341000E-01 3.7500000E-01 1.0792000E+01 3.4653800E+02 2.2719900E+09 4.8080200E+09", + "2.9595000E-01 3.7500000E-01 1.0232000E+01 3.3933300E+02 2.0500500E+09 4.5014000E+09", + "3.2846000E-01 3.7500000E-01 9.6720000E+00 3.3000400E+02 1.8282500E+09 4.2440700E+09", + "3.6098000E-01 3.7500000E-01 9.1100000E+00 3.2199000E+02 1.5887100E+09 3.9952800E+09", + "3.9350000E-01 3.7500000E-01 8.5340000E+00 3.1382000E+02 1.3619300E+09 3.7507600E+09", + "4.2602000E-01 3.7500000E-01 7.9320000E+00 2.9473400E+02 1.1023800E+09 3.4471400E+09", + "4.5855000E-01 3.7500000E-01 7.3210000E+00 2.8712000E+02 8.7580000E+08 3.1390700E+09", + "4.9106000E-01 3.7500000E-01 6.7110000E+00 2.6334300E+02 6.8130000E+08 2.7342400E+09", + "5.2358000E-01 3.7500000E-01 6.1220000E+00 2.5320700E+02 5.3472000E+08 2.5548700E+09", + "5.5610000E-01 3.7500000E-01 5.5460000E+00 2.4166600E+02 4.0890000E+08 2.3340300E+09", + "5.8862000E-01 3.7500000E-01 4.9710000E+00 2.2063800E+02 3.1454000E+08 1.8287300E+09", + "6.2115000E-01 3.7500000E-01 4.4010000E+00 2.0029300E+02 2.3863000E+08 1.5841000E+09", + "6.5366000E-01 3.7500000E-01 3.8340000E+00 1.7940400E+02 1.7588000E+08 1.3233600E+09", + "6.8618000E-01 3.7500000E-01 3.3320000E+00 1.6509400E+02 1.2601000E+08 1.1836800E+09", + "7.1870000E-01 3.7500000E-01 2.8900000E+00 1.5441100E+02 1.0726000E+08 1.0201600E+09", + "7.5122000E-01 3.7500000E-01 2.5030000E+00 1.3893500E+02 9.0880000E+07 7.9781000E+08", + "7.8376000E-01 3.7500000E-01 2.1160000E+00 1.2955500E+02 7.6310000E+07 7.0961000E+08", + "8.1626000E-01 3.7500000E-01 1.7300000E+00 1.0726400E+02 6.1050000E+07 5.1819000E+08", + "8.4878000E-01 3.7500000E-01 1.3420000E+00 9.8776000E+01 4.9480000E+07 4.5487000E+08", + "8.8130000E-01 3.7500000E-01 9.5400000E-01 9.0248000E+01 3.9360000E+07 3.9512000E+08", + "8.9756000E-01 3.7500000E-01 7.6000000E-01 8.3001000E+01 3.4670000E+07 3.5372000E+08", + "9.1382000E-01 3.7500000E-01 5.7400000E-01 7.2906000E+01 3.0410000E+07 3.0473000E+08", + "9.3008000E-01 3.7500000E-01 4.0400000E-01 6.8772000E+01 2.6520000E+07 2.8142000E+08", + "9.3821000E-01 3.7500000E-01 3.1900000E-01 6.6264000E+01 2.3840000E+07 2.6171000E+08", + "9.4636000E-01 3.7500000E-01 2.5300000E-01 5.9340000E+01 1.9630000E+07 1.5881000E+08", + "9.5447000E-01 3.7500000E-01 2.1600000E-01 5.5914000E+01 1.6000000E+07 1.3788000E+08", + "9.6260000E-01 3.7500000E-01 1.7800000E-01 5.2484000E+01 1.2830000E+07 1.1879000E+08", + "9.7073000E-01 3.7500000E-01 1.4000000E-01 4.9114000E+01 1.0080000E+07 1.0163000E+08", + "9.7886000E-01 3.7500000E-01 1.0100000E-01 4.5818000E+01 7.5500000E+06 8.5070000E+07", + "9.8699000E-01 3.7500000E-01 6.2000000E-02 4.1669000E+01 4.6000000E+06 6.4260000E+07", + "9.9512000E-01 3.7500000E-01 2.3000000E-02 1.1453000E+01 2.5000000E+05 6.6100000E+06", + "1.0000000E+00 3.7500000E-01 0.0000000E+00 1.0319000E+01 1.7000000E+05 5.0100000E+06", + "---------------------- BLADE MODE SHAPES ---------------------------------------", + " 0.0622 BldFl1Sh(2) - Flap mode 1, coeff of x^2", + " 1.7254 BldFl1Sh(3) - , coeff of x^3", + " -3.2452 BldFl1Sh(4) - , coeff of x^4", + " 4.7131 BldFl1Sh(5) - , coeff of x^5", + " -2.2555 BldFl1Sh(6) - , coeff of x^6", + " -0.5809 BldFl2Sh(2) - Flap mode 2, coeff of x^2", + " 1.2067 BldFl2Sh(3) - , coeff of x^3", + " -15.5349 BldFl2Sh(4) - , coeff of x^4", + " 29.7347 BldFl2Sh(5) - , coeff of x^5", + " -13.8255 BldFl2Sh(6) - , coeff of x^6", + " 0.3627 BldEdgSh(2) - Edge mode 1, coeff of x^2", + " 2.5337 BldEdgSh(3) - , coeff of x^3", + " -3.5772 BldEdgSh(4) - , coeff of x^4", + " 2.376 BldEdgSh(5) - , coeff of x^5", + " -0.6952 BldEdgSh(6) - , coeff of x^6", + "", + "" + ] + }, + { + "Name": "NREL_5MW_Monopile_ElastoDyn_Tower.dat", + "Type": "Misc", + "Lines": [ + "------- ELASTODYN V1.00.* TOWER INPUT FILE -------------------------------------", + "NREL 5.0 MW offshore baseline monopile tower for flexible monopile modeled in SubDyn.", + "---------------------- TOWER PARAMETERS ----------------------------------------", + " 11 NTwInpSt - Number of input stations to specify tower geometry", + " 1.0 TwrFADmp(1) - Tower 1st fore-aft mode structural damping ratio (%)", + " 1.0 TwrFADmp(2) - Tower 2nd fore-aft mode structural damping ratio (%)", + " 1.0 TwrSSDmp(1) - Tower 1st side-to-side mode structural damping ratio (%)", + " 1.0 TwrSSDmp(2) - Tower 2nd side-to-side mode structural damping ratio (%)", + "---------------------- TOWER ADJUSTMUNT FACTORS --------------------------------", + " 1.0 FAStTunr(1) - Tower fore-aft modal stiffness tuner, 1st mode (-)", + " 1.0 FAStTunr(2) - Tower fore-aft modal stiffness tuner, 2nd mode (-)", + " 1.0 SSStTunr(1) - Tower side-to-side stiffness tuner, 1st mode (-)", + " 1.0 SSStTunr(2) - Tower side-to-side stiffness tuner, 2nd mode (-)", + " 1.0 AdjTwMa - Factor to adjust tower mass density (-)", + " 1.0 AdjFASt - Factor to adjust tower fore-aft stiffness (-)", + " 1.0 AdjSSSt - Factor to adjust tower side-to-side stiffness (-)", + "---------------------- DISTRIBUTED TOWER PROPERTIES ----------------------------", + "HtFract TMassDen TwFAStif TwSSStif", + " (-) (kg/m) (Nm^2) (Nm^2)", + "0.0 4.3065100E+03 4.7449000E+11 4.7449000E+11", + "1.0E-01 4.0304400E+03 4.1308000E+11 4.1308000E+11", + "2.0E-01 3.7634500E+03 3.5783000E+11 3.5783000E+11", + "3.0E-01 3.5055200E+03 3.0830000E+11 3.0830000E+11", + "4.0E-01 3.2566600E+03 2.6408000E+11 2.6408000E+11", + "5.0E-01 3.0168600E+03 2.2480000E+11 2.2480000E+11", + "6.0E-01 2.7861300E+03 1.9006000E+11 1.9006000E+11", + "7.0E-01 2.5644600E+03 1.5949000E+11 1.5949000E+11", + "8.0E-01 2.3518700E+03 1.3277000E+11 1.3277000E+11", + "9.0E-01 2.1483400E+03 1.0954000E+11 1.0954000E+11", + "1.0E+00 1.9538700E+03 8.9490000E+10 8.9490000E+10", + "---------------------- TOWER FORE-AFT MODE SHAPES ------------------------------", + " 0.9877 TwFAM1Sh(2) - Mode 1, coefficient of x^2 term", + " 0.1608 TwFAM1Sh(3) - , coefficient of x^3 term", + " -0.1884 TwFAM1Sh(4) - , coefficient of x^4 term", + " 0.1508 TwFAM1Sh(5) - , coefficient of x^5 term", + " -0.1108 TwFAM1Sh(6) - , coefficient of x^6 term", + " -1.0297 TwFAM2Sh(2) - Mode 2, coefficient of x^2 term", + " 1.4443 TwFAM2Sh(3) - , coefficient of x^3 term", + " 0.8883 TwFAM2Sh(4) - , coefficient of x^4 term", + " -0.1276 TwFAM2Sh(5) - , coefficient of x^5 term", + " -0.1752 TwFAM2Sh(6) - , coefficient of x^6 term", + "---------------------- TOWER SIDE-TO-SIDE MODE SHAPES --------------------------", + " 0.9792 TwSSM1Sh(2) - Mode 1, coefficient of x^2 term", + " 0.1618 TwSSM1Sh(3) - , coefficient of x^3 term", + " -0.1797 TwSSM1Sh(4) - , coefficient of x^4 term", + " 0.1453 TwSSM1Sh(5) - , coefficient of x^5 term", + " -0.1065 TwSSM1Sh(6) - , coefficient of x^6 term", + " -1.2253 TwSSM2Sh(2) - Mode 2, coefficient of x^2 term", + " 1.3297 TwSSM2Sh(3) - , coefficient of x^3 term", + " 1.0340 TwSSM2Sh(4) - , coefficient of x^4 term", + " -0.1508 TwSSM2Sh(5) - , coefficient of x^5 term", + " 0.0123 TwSSM2Sh(6) - , coefficient of x^6 term", + "", + "" + ] + }, + { + "Name": "NREL_5MW_AeroDyn_blade.dat", + "Type": "Misc", + "Lines": [ + "------- AERODYN v15.00.* BLADE DEFINITION INPUT FILE -------------------------------------", + "NREL 5.0 MW offshore baseline aerodynamic blade input properties; note that we need to add the aerodynamic center to this file", + "====== Blade Properties =================================================================", + " 19 NumBlNds - Number of blade nodes used in the analysis (-)", + " BlSpn BlCrvAC BlSwpAC BlCrvAng BlTwist BlChord BlAFID BlCb BlCenBn BlCenBt", + " (m) (m) (m) (deg) (deg) (m) (-) (-) (m) (m)", + "0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 1.3308000E+01 3.5420000E+00 1 0.0 0.0 0.0", + "1.3667000E+00 -8.1531745E-04 -3.4468858E-03 0.0000000E+00 1.3308000E+01 3.5420000E+00 1 0.0 0.0 0.0", + "4.1000000E+00 -2.4839790E-02 -1.0501421E-01 0.0000000E+00 1.3308000E+01 3.8540000E+00 1 0.0 0.0 0.0", + "6.8333000E+00 -5.9469375E-02 -2.5141635E-01 0.0000000E+00 1.3308000E+01 4.1670000E+00 2 0.0 0.0 0.0", + "1.0250000E+01 -1.0909141E-01 -4.6120149E-01 0.0000000E+00 1.3308000E+01 4.5570000E+00 3 0.0 0.0 0.0", + "1.4350000E+01 -1.1573354E-01 -5.6986665E-01 0.0000000E+00 1.1480000E+01 4.6520000E+00 4 0.0 0.0 0.0", + "1.8450000E+01 -9.8316709E-02 -5.4850833E-01 0.0000000E+00 1.0162000E+01 4.4580000E+00 4 0.0 0.0 0.0", + "2.2550000E+01 -8.3186967E-02 -5.2457001E-01 0.0000000E+00 9.0110000E+00 4.2490000E+00 5 0.0 0.0 0.0", + "2.6650000E+01 -6.7933232E-02 -4.9624675E-01 0.0000000E+00 7.7950000E+00 4.0070000E+00 6 0.0 0.0 0.0", + "3.0750000E+01 -5.3393159E-02 -4.6544755E-01 0.0000000E+00 6.5440000E+00 3.7480000E+00 6 0.0 0.0 0.0", + "3.4850000E+01 -4.0899260E-02 -4.3583519E-01 0.0000000E+00 5.3610000E+00 3.5020000E+00 7 0.0 0.0 0.0", + "3.8950000E+01 -2.9722933E-02 -4.0591323E-01 0.0000000E+00 4.1880000E+00 3.2560000E+00 7 0.0 0.0 0.0", + "4.3050000E+01 -2.0511081E-02 -3.7569051E-01 0.0000000E+00 3.1250000E+00 3.0100000E+00 8 0.0 0.0 0.0", + "4.7150000E+01 -1.3980013E-02 -3.4521705E-01 0.0000000E+00 2.3190000E+00 2.7640000E+00 8 0.0 0.0 0.0", + "5.1250000E+01 -8.3819737E-03 -3.1463837E-01 0.0000000E+00 1.5260000E+00 2.5180000E+00 8 0.0 0.0 0.0", + "5.4666700E+01 -4.3546914E-03 -2.8909220E-01 0.0000000E+00 8.6300000E-01 2.3130000E+00 8 0.0 0.0 0.0", + "5.7400000E+01 -1.6838383E-03 -2.6074456E-01 0.0000000E+00 3.7000000E-01 2.0860000E+00 8 0.0 0.0 0.0", + "6.0133300E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 0.0 0.0 0.0", + "6.1499900E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 0.0 0.0 0.0", + "", + "!bjj: because of precision in the BD-AD coupling, 61.5m didn't work, so I changed it to 61.4999m", + "6.1500000E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 0.0 0.0 0.0" + ] + } + ], + "StControl": [], + "AirfoilInfo": [ + { + "Name": "Cylinder1.dat", + "Type": "AirfoilInfo", + "Lines": [ + "! ------------ AirfoilInfo v1.01.x Input File ----------------------------------", + "! Round root section with a Cd of 0.50", + "! Made by Jason Jonkman", + "! note that this file uses Marshall Buhl's new input file processing; start all comment lines with !", + "! ------------------------------------------------------------------------------", + "\"DEFAULT\" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; \"default\"} [default=1]", + " 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)", + " 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included.", + "! ......... x-y coordinates are next if NumCoords \u003e 0 .............", + "! x-y coordinate of airfoil reference", + "! x/c y/c", + "0.5 0", + "! coordinates of airfoil shape", + "! cylinder (interpolated to 399 points)", + "! x/c y/c", + "1.000000 0.000000", + "0.996600 0.058210", + "0.993140 0.082541", + "0.989610 0.101400", + "0.986010 0.117449", + "0.982350 0.131676", + "0.978630 0.144614", + "0.974840 0.156611", + "0.970980 0.167863", + "0.967060 0.178480", + "0.963070 0.188590", + "0.959020 0.198244", + "0.954900 0.207523", + "0.950720 0.216452", + "0.946470 0.225088", + "0.942160 0.233441", + "0.937780 0.241555", + "0.933330 0.249450", + "0.928820 0.257125", + "0.924250 0.264598", + "0.919610 0.271896", + "0.914900 0.279030", + "0.910130 0.285995", + "0.905290 0.292814", + "0.900390 0.299479", + "0.895420 0.306011", + "0.890390 0.312403", + "0.885290 0.318672", + "0.880130 0.324809", + "0.874900 0.330832", + "0.869610 0.336732", + 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"0.623330 -0.484551", + "0.630000 -0.482804", + "0.636670 -0.480959", + "0.643330 -0.479016", + "0.650000 -0.476970", + "0.656670 -0.474821", + "0.663330 -0.472571", + "0.670000 -0.470213", + "0.676670 -0.467747", + "0.683330 -0.465178", + "0.690000 -0.462493", + "0.696670 -0.459697", + "0.703330 -0.456790", + "0.710000 -0.453762", + "0.716670 -0.450615", + "0.723330 -0.447352", + "0.730000 -0.443959", + "0.736670 -0.440440", + "0.743330 -0.436796", + "0.750000 -0.433013", + "0.756600 -0.429135", + "0.763140 -0.425156", + "0.769610 -0.421082", + "0.776010 -0.416915", + "0.782350 -0.412648", + "0.788630 -0.408280", + "0.794840 -0.403818", + "0.800980 -0.399263", + "0.807060 -0.394606", + "0.813070 -0.389855", + "0.819020 -0.385002", + "0.824900 -0.380053", + "0.830720 -0.374999", + "0.836470 -0.369849", + "0.842160 -0.364591", + "0.847780 -0.359234", + "0.853330 -0.353777", + "0.858820 -0.348207", + "0.864250 -0.342523", + "0.869610 -0.336732", + "0.874900 -0.330832", + "0.880130 -0.324809", + "0.885290 -0.318672", + "0.890390 -0.312403", + "0.895420 -0.306011", + "0.900390 -0.299479", + "0.905290 -0.292814", + "0.910130 -0.285995", + "0.914900 -0.279030", + "0.919610 -0.271896", + "0.924250 -0.264598", + "0.928820 -0.257125", + "0.933330 -0.249450", + "0.937780 -0.241555", + "0.942160 -0.233441", + "0.946470 -0.225088", + "0.950720 -0.216452", + "0.954900 -0.207523", + "0.959020 -0.198244", + "0.963070 -0.188590", + "0.967060 -0.178480", + "0.970980 -0.167863", + "0.974840 -0.156611", + "0.978630 -0.144614", + "0.982350 -0.131676", + "0.986010 -0.117449", + "0.989610 -0.101400", + "0.993140 -0.082541", + "0.996600 -0.058210", + "1.000000 0.000000", + "\"unused\" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + " 1 NumTabs ! Number of airfoil tables in this file.", + "! ------------------------------------------------------------------------------", + "! data for table 1", + "! ------------------------------------------------------------------------------", + " 0.75 Re ! Reynolds number in millions", + " 0 UserProp ! User property (control) setting", + "True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line", + "!........................................", + " 0 alpha0 ! 0-lift angle of attack, depends on airfoil.", + " 0 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003ealpha0. (deg)", + " 0 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003calpha0. (deg)", + " 0 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)", + " 0 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)", + " 3 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]", + " 6 T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on Re,M, and airfoil class. [default = 6]", + " 1.7 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]", + " 11 T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]", + " 0.14 b1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.14]", + " 0.53 b2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.53]", + " 5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]", + " 0.3 A1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.3]", + " 0.7 A2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.7]", + " 1 A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]", + " 0 S1 ! Constant in the f curve best-fit for alpha0\u003c=AOA\u003c=alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S2 ! Constant in the f curve best-fit for AOA\u003e alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S3 ! Constant in the f curve best-fit for alpha2\u003c=AOA\u003c alpha0; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S4 ! Constant in the f curve best-fit for AOA\u003c alpha2; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.", + " 0 Cn2 ! As Cn1 for negative AOAs.", + " 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19]", + " 0.5 Cd0 ! 2D drag coefficient value at 0-lift.", + " 0 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0]", + " 0 k0 ! Constant in the \\hat(x)_cp curve best-fit; = (\\hat(x)_AC-0.25). [ignored if UAMod\u003c\u003e1]", + " 0 k1 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k2 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k3 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod\u003c\u003e1]", + " 0.2 x_cp_bar ! Constant in the expression of \\hat(x)_cp^v. [ignored if UAMod\u003c\u003e1, default = 0.2]", + "\"DEFAULT\" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string \"Default\" sets UACutout to 45 degrees]", + "\"DEFAULT\" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5]", + "!........................................", + "! Table of aerodynamics coefficients", + " 3 NumAlf ! Number of data lines in the following table", + "! Alpha Cl Cd Cm", + "! (deg) (-) (-) (-)", + " -180.00 0.000 0.5000 0.0", + " 0.00 0.000 0.5000 0.0", + " 180.00 0.000 0.5000 0.0", + "! ------------------------------------------------------------------------------", + "" + ], + "BL_File": { + "Name": "BL_File", + "Type": "Path", + "Desc": "The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + "Line": 415, + "Value": "FileNotFound", + "FileType": "", + "Root": false + } + }, + { + "Name": "Cylinder2.dat", + "Type": "AirfoilInfo", + "Lines": [ + "! ------------ AirfoilInfo v1.01.x Input File ----------------------------------", + "! Round root section with a Cd of 0.35", + "! Made by Jason Jonkman", + "! note that this file uses Marshall Buhl's new input file processing; start all comment lines with !", + "! ------------------------------------------------------------------------------", + "\"DEFAULT\" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; \"default\"} [default=1]", + " 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)", + " 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included.", + "! ......... x-y coordinates are next if NumCoords \u003e 0 .............", + "! x-y coordinate of airfoil reference", + "! x/c y/c", + "0.41667 0", + "! coordinates of airfoil shape", + "! cylinder (interpolated to 399 points)", + "! x/c y/c", + "1.000000 0.000000", + "0.996600 0.058210", + "0.993140 0.082541", + "0.989610 0.101400", + "0.986010 0.117449", + "0.982350 0.131676", + "0.978630 0.144614", + "0.974840 0.156611", + "0.970980 0.167863", + "0.967060 0.178480", + "0.963070 0.188590", + "0.959020 0.198244", + "0.954900 0.207523", + "0.950720 0.216452", + "0.946470 0.225088", + "0.942160 0.233441", + "0.937780 0.241555", + "0.933330 0.249450", + "0.928820 0.257125", + "0.924250 0.264598", + "0.919610 0.271896", + "0.914900 0.279030", + "0.910130 0.285995", + "0.905290 0.292814", + "0.900390 0.299479", + "0.895420 0.306011", + "0.890390 0.312403", + "0.885290 0.318672", + "0.880130 0.324809", + "0.874900 0.330832", + "0.869610 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"0.343330 -0.474821", + "0.350000 -0.476970", + "0.356670 -0.479016", + "0.363330 -0.480959", + "0.370000 -0.482804", + "0.376670 -0.484551", + "0.383330 -0.486198", + "0.390000 -0.487750", + "0.396670 -0.489206", + "0.403330 -0.490566", + "0.410000 -0.491833", + "0.416670 -0.493007", + "0.423330 -0.494087", + "0.430000 -0.495076", + "0.436670 -0.495973", + "0.443330 -0.496778", + "0.450000 -0.497494", + "0.456670 -0.498119", + "0.463330 -0.498653", + "0.470000 -0.499099", + "0.476670 -0.499455", + "0.483330 -0.499722", + "0.490000 -0.499900", + "0.496670 -0.499989", + "0.503330 -0.499989", + "0.510000 -0.499900", + "0.516670 -0.499722", + "0.523330 -0.499455", + "0.530000 -0.499099", + "0.536670 -0.498653", + "0.543330 -0.498119", + "0.550000 -0.497494", + "0.556670 -0.496778", + "0.563330 -0.495973", + "0.570000 -0.495076", + "0.576670 -0.494087", + "0.583330 -0.493007", + "0.590000 -0.491833", + "0.596669 -0.490566", + "0.603330 -0.489206", + "0.610000 -0.487750", + "0.616670 -0.486198", + "0.623330 -0.484551", + "0.630000 -0.482804", + "0.636670 -0.480959", + "0.643330 -0.479016", + "0.650000 -0.476970", + "0.656670 -0.474821", + "0.663330 -0.472571", + "0.670000 -0.470213", + "0.676670 -0.467747", + "0.683330 -0.465178", + "0.690000 -0.462493", + "0.696670 -0.459697", + "0.703330 -0.456790", + "0.710000 -0.453762", + "0.716670 -0.450615", + "0.723330 -0.447352", + "0.730000 -0.443959", + "0.736670 -0.440440", + "0.743330 -0.436796", + "0.750000 -0.433013", + "0.756600 -0.429135", + "0.763140 -0.425156", + "0.769610 -0.421082", + "0.776010 -0.416915", + "0.782350 -0.412648", + "0.788630 -0.408280", + "0.794840 -0.403818", + "0.800980 -0.399263", + "0.807060 -0.394606", + "0.813070 -0.389855", + "0.819020 -0.385002", + "0.824900 -0.380053", + "0.830720 -0.374999", + "0.836470 -0.369849", + "0.842160 -0.364591", + "0.847780 -0.359234", + "0.853330 -0.353777", + "0.858820 -0.348207", + "0.864250 -0.342523", + "0.869610 -0.336732", + "0.874900 -0.330832", + "0.880130 -0.324809", + "0.885290 -0.318672", + "0.890390 -0.312403", + "0.895420 -0.306011", + "0.900390 -0.299479", + "0.905290 -0.292814", + "0.910130 -0.285995", + "0.914900 -0.279030", + "0.919610 -0.271896", + "0.924250 -0.264598", + "0.928820 -0.257125", + "0.933330 -0.249450", + "0.937780 -0.241555", + "0.942160 -0.233441", + "0.946470 -0.225088", + "0.950720 -0.216452", + "0.954900 -0.207523", + "0.959020 -0.198244", + "0.963070 -0.188590", + "0.967060 -0.178480", + "0.970980 -0.167863", + "0.974840 -0.156611", + "0.978630 -0.144614", + "0.982350 -0.131676", + "0.986010 -0.117449", + "0.989610 -0.101400", + "0.993140 -0.082541", + "0.996600 -0.058210", + "1.000000 0.000000", + "! ......... x-y coordinates are next if NumCoords \u003e 0 .............", + "\"unused\" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + " 1 NumTabs ! Number of airfoil tables in this file.", + "! ------------------------------------------------------------------------------", + "! data for table 1", + "! ------------------------------------------------------------------------------", + " 0.75 Re ! Reynolds number in millions", + " 0 UserProp ! User property (control) setting", + "True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line", + "!........................................", + " 0 alpha0 ! 0-lift angle of attack, depends on airfoil.", + " 0 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003ealpha0. (deg)", + " 0 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003calpha0. (deg)", + " 0 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)", + " 0 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)", + " 3 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]", + " 6 T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on Re,M, and airfoil class. [default = 6]", + " 1.7 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]", + " 11 T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]", + " 0.14 b1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.14]", + " 0.53 b2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.53]", + " 5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]", + " 0.3 A1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.3]", + " 0.7 A2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.7]", + " 1 A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]", + " 0 S1 ! Constant in the f curve best-fit for alpha0\u003c=AOA\u003c=alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S2 ! Constant in the f curve best-fit for AOA\u003e alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S3 ! Constant in the f curve best-fit for alpha2\u003c=AOA\u003c alpha0; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S4 ! Constant in the f curve best-fit for AOA\u003c alpha2; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.", + " 0 Cn2 ! As Cn1 for negative AOAs.", + " 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19]", + " 0.35 Cd0 ! 2D drag coefficient value at 0-lift.", + " 0 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0]", + " 0 k0 ! Constant in the \\hat(x)_cp curve best-fit; = (\\hat(x)_AC-0.25). [ignored if UAMod\u003c\u003e1]", + " 0 k1 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k2 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k3 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod\u003c\u003e1]", + " 0.2 x_cp_bar ! Constant in the expression of \\hat(x)_cp^v. [ignored if UAMod\u003c\u003e1, default = 0.2]", + "\"DEFAULT\" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string \"Default\" sets UACutout to 45 degrees]", + "\"DEFAULT\" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5]", + "!........................................", + "! Table of aerodynamics coefficients", + " 3 NumAlf ! Number of data lines in the following table", + "! Alpha Cl Cd Cm", + "! (deg) (-) (-) (-)", + " -180.00 0.000 0.3500 0.0", + " 0.00 0.000 0.3500 0.0", + " 180.00 0.000 0.3500 0.0", + "! ------------------------------------------------------------------------------", + "" + ], + "BL_File": { + "Name": "BL_File", + "Type": "Path", + "Desc": "The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + "Line": 416, + "Value": "FileNotFound", + "FileType": "", + "Root": false + } + }, + { + "Name": "DU40_A17.dat", + "Type": "AirfoilInfo", + "Lines": [ + "! ------------ AirfoilInfo v1.01.x Input File ----------------------------------", + "! DU40 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN).", + "! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls.", + "! note that this file uses Marshall Buhl's new input file processing; start all comment lines with !", + "! ------------------------------------------------------------------------------", + "\"DEFAULT\" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; \"default\"} [default=1]", + " 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)", + " 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included.", + "! ......... x-y coordinates are next if NumCoords \u003e 0 .............", + "! x-y coordinate of airfoil reference", + "! x/c y/c", + "0.33087 0", + "! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2\u0026t=440", + "! Adjusted DU4050", + "! x/c y/c", + "1.00000 0.00347", + "0.99660 0.00455", + "0.99314 0.00565", + "0.98961 0.00678", + "0.98601 0.00795", + "0.98235 0.00914", + "0.97863 0.01035", + "0.97484 0.01158", + "0.97098 0.01283", + "0.96706 0.01410", + "0.96307 0.01539", + "0.95902 0.01670", + "0.95490 0.01803", + "0.95072 0.01937", + "0.94647 0.02074", + "0.94216 0.02212", + "0.93778 0.02352", + "0.93333 0.02495", + "0.92882 0.02639", + "0.92425 0.02786", + "0.91961 0.02936", + "0.91490 0.03087", + "0.91013 0.03242", + "0.90529 0.03400", + "0.90039 0.03560", + "0.89542 0.03723", + "0.89039 0.03887", + "0.88529 0.04056", + "0.88013 0.04226", + "0.87490 0.04399", + "0.86961 0.04575", + "0.86425 0.04754", + "0.85882 0.04935", + "0.85333 0.05119", + "0.84778 0.05305", + "0.84216 0.05493", + "0.83647 0.05685", + "0.83072 0.05878", + "0.82490 0.06076", + "0.81902 0.06275", + "0.81307 0.06476", + "0.80706 0.06680", + "0.80098 0.06886", + "0.79484 0.07094", + "0.78863 0.07304", + "0.78235 0.07517", + 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+ "0.29667 -0.21502", + "0.30333 -0.21476", + "0.31000 -0.21437", + "0.31667 -0.21384", + "0.32333 -0.21320", + "0.33000 -0.21243", + "0.33667 -0.21155", + "0.34333 -0.21057", + "0.35000 -0.20948", + "0.35667 -0.20827", + "0.36333 -0.20697", + "0.37000 -0.20556", + "0.37667 -0.20407", + "0.38333 -0.20248", + "0.39000 -0.20081", + "0.39667 -0.19904", + "0.40333 -0.19720", + "0.41000 -0.19527", + "0.41667 -0.19327", + "0.42333 -0.19119", + "0.43000 -0.18905", + "0.43667 -0.18683", + "0.44333 -0.18454", + "0.45000 -0.18219", + "0.45667 -0.17976", + "0.46333 -0.17727", + "0.47000 -0.17473", + "0.47667 -0.17212", + "0.48333 -0.16945", + "0.49000 -0.16673", + "0.49667 -0.16397", + "0.50333 -0.16115", + "0.51000 -0.15828", + "0.51667 -0.15537", + "0.52333 -0.15242", + "0.53000 -0.14942", + "0.53667 -0.14639", + "0.54333 -0.14333", + "0.55000 -0.14024", + "0.55667 -0.13713", + "0.56333 -0.13399", + "0.57000 -0.13083", + "0.57667 -0.12765", + "0.58333 -0.12446", + "0.59000 -0.12125", + "0.59667 -0.11804", + "0.60333 -0.11482", + "0.61000 -0.11160", + "0.61667 -0.10838", + "0.62333 -0.10515", + "0.63000 -0.10192", + "0.63667 -0.09870", + "0.64333 -0.09549", + "0.65000 -0.09228", + "0.65667 -0.08909", + "0.66333 -0.08590", + "0.67000 -0.08274", + "0.67667 -0.07958", + "0.68333 -0.07645", + "0.69000 -0.07333", + "0.69667 -0.07024", + "0.70333 -0.06717", + "0.71000 -0.06413", + "0.71667 -0.06112", + "0.72333 -0.05814", + "0.73000 -0.05519", + "0.73667 -0.05228", + "0.74333 -0.04941", + "0.75000 -0.04658", + "0.75660 -0.04382", + "0.76314 -0.04114", + "0.76961 -0.03853", + "0.77601 -0.03600", + "0.78235 -0.03354", + "0.78863 -0.03116", + "0.79484 -0.02887", + "0.80098 -0.02665", + "0.80706 -0.02452", + "0.81307 -0.02247", + "0.81902 -0.02050", + "0.82490 -0.01862", + "0.83072 -0.01681", + "0.83647 -0.01510", + "0.84216 -0.01346", + "0.84778 -0.01191", + "0.85333 -0.01045", + "0.85882 -0.00907", + "0.86425 -0.00776", + "0.86961 -0.00653", + "0.87490 -0.00539", + "0.88013 -0.00434", + "0.88529 -0.00335", + "0.89039 -0.00245", + "0.89542 -0.00160", + "0.90039 -0.00085", + "0.90529 -0.00015", + "0.91013 0.00046", + "0.91490 0.00103", + "0.91961 0.00151", + "0.92425 0.00193", + "0.92882 0.00229", + "0.93333 0.00258", + "0.93778 0.00279", + "0.94216 0.00295", + "0.94647 0.00303", + "0.95072 0.00303", + "0.95490 0.00296", + "0.95902 0.00282", + "0.96307 0.00261", + "0.96706 0.00232", + "0.97098 0.00194", + "0.97484 0.00149", + "0.97863 0.00098", + "0.98235 0.00040", + "0.98601 -0.00025", + "0.98961 -0.00097", + "0.99314 -0.00176", + "0.99660 -0.00261", + "1.00000 -0.00347", + "\"unused\" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + " 1 NumTabs ! Number of airfoil tables in this file.", + "! ------------------------------------------------------------------------------", + "! data for table 1", + "! ------------------------------------------------------------------------------", + " 0.75 Re ! Reynolds number in millions", + " 0 UserProp ! User property (control) setting", + "True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line", + "!........................................", + " -3.2 alpha0 ! 0-lift angle of attack, depends on airfoil.", + " 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003ealpha0. (deg)", + " -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003calpha0. (deg)", + " 1 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)", + " 7.4888 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)", + " 3 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]", + " 6 T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on Re,M, and airfoil class. [default = 6]", + " 1.7 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]", + " 11 T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]", + " 0.14 b1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.14]", + " 0.53 b2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.53]", + " 5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]", + " 0.3 A1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.3]", + " 0.7 A2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.7]", + " 1 A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]", + " 0 S1 ! Constant in the f curve best-fit for alpha0\u003c=AOA\u003c=alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S2 ! Constant in the f curve best-fit for AOA\u003e alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S3 ! Constant in the f curve best-fit for alpha2\u003c=AOA\u003c alpha0; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S4 ! Constant in the f curve best-fit for AOA\u003c alpha2; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 1.3519 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.", + " -0.3226 Cn2 ! As Cn1 for negative AOAs.", + " 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19]", + " 0.03 Cd0 ! 2D drag coefficient value at 0-lift.", + " -0.05 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0]", + " 0 k0 ! Constant in the \\hat(x)_cp curve best-fit; = (\\hat(x)_AC-0.25). [ignored if UAMod\u003c\u003e1]", + " 0 k1 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k2 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k3 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod\u003c\u003e1]", + " 0.2 x_cp_bar ! Constant in the expression of \\hat(x)_cp^v. [ignored if UAMod\u003c\u003e1, default = 0.2]", + "\"DEFAULT\" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string \"Default\" sets UACutout to 45 degrees]", + "\"DEFAULT\" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5]", + "!........................................", + "! Table of aerodynamics coefficients", + " 136 NumAlf ! Number of data lines in the following table", + "! Alpha Cl Cd Cm", + "! (deg) (-) (-) (-)", + " -180.00 0.000 0.0602 0.0000", + " -175.00 0.218 0.0699 0.0934", + " -170.00 0.397 0.1107 0.1697", + " -160.00 0.642 0.3045 0.2813", + " -155.00 0.715 0.4179 0.3208", + " -150.00 0.757 0.5355 0.3516", + " -145.00 0.772 0.6535 0.3752", + " -140.00 0.762 0.7685 0.3926", + " -135.00 0.731 0.8777 0.4048", + " -130.00 0.680 0.9788 0.4126", + " -125.00 0.613 1.0700 0.4166", + " -120.00 0.532 1.1499 0.4176", + " -115.00 0.439 1.2174 0.4158", + " -110.00 0.337 1.2716 0.4117", + " -105.00 0.228 1.3118 0.4057", + " -100.00 0.114 1.3378 0.3979", + " -95.00 -0.002 1.3492 0.3887", + " -90.00 -0.120 1.3460 0.3781", + " -85.00 -0.236 1.3283 0.3663", + " -80.00 -0.349 1.2964 0.3534", + " -75.00 -0.456 1.2507 0.3394", + " -70.00 -0.557 1.1918 0.3244", + " -65.00 -0.647 1.1204 0.3084", + " -60.00 -0.727 1.0376 0.2914", + " -55.00 -0.792 0.9446 0.2733", + " -50.00 -0.842 0.8429 0.2543", + " -45.00 -0.874 0.7345 0.2342", + " -40.00 -0.886 0.6215 0.2129", + " -35.00 -0.875 0.5067 0.1906", + " -30.00 -0.839 0.3932 0.1670", + " -25.00 -0.777 0.2849 0.1422", + " -24.00 -0.761 0.2642 0.1371", + " -23.00 -0.744 0.2440 0.1320", + " -22.00 -0.725 0.2242 0.1268", + " -21.00 -0.706 0.2049 0.1215", + " -20.00 -0.685 0.1861 0.1162", + " -19.00 -0.662 0.1687 0.1097", + " -18.00 -0.635 0.1533 0.1012", + " -17.00 -0.605 0.1398 0.0907", + " -16.00 -0.571 0.1281 0.0784", + " -15.00 -0.534 0.1183 0.0646", + " -14.00 -0.494 0.1101 0.0494", + " -13.00 -0.452 0.1036 0.0330", + " -12.00 -0.407 0.0986 0.0156", + " -11.00 -0.360 0.0951 -0.0026", + " -10.00 -0.311 0.0931 -0.0213", + " -8.00 -0.208 0.0930 -0.0600", + " -6.00 -0.111 0.0689 -0.0500", + " -5.50 -0.090 0.0614 -0.0516", + " -5.00 -0.072 0.0547 -0.0532", + " -4.50 -0.065 0.0480 -0.0538", + " -4.00 -0.054 0.0411 -0.0544", + " -3.50 -0.017 0.0349 -0.0554", + " -3.00 0.003 0.0299 -0.0558", + " -2.50 0.014 0.0255 -0.0555", + " -2.00 0.009 0.0198 -0.0534", + " -1.50 0.004 0.0164 -0.0442", + " -1.00 0.036 0.0147 -0.0469", + " -0.50 0.073 0.0137 -0.0522", + " 0.00 0.137 0.0113 -0.0573", + " 0.50 0.213 0.0114 -0.0644", + " 1.00 0.292 0.0118 -0.0718", + " 1.50 0.369 0.0122 -0.0783", + " 2.00 0.444 0.0124 -0.0835", + " 2.50 0.514 0.0124 -0.0866", + " 3.00 0.580 0.0123 -0.0887", + " 3.50 0.645 0.0120 -0.0900", + " 4.00 0.710 0.0119 -0.0914", + " 4.50 0.776 0.0122 -0.0933", + " 5.00 0.841 0.0125 -0.0947", + " 5.50 0.904 0.0129 -0.0957", + " 6.00 0.967 0.0135 -0.0967", + " 6.50 1.027 0.0144 -0.0973", + " 7.00 1.084 0.0158 -0.0972", + " 7.50 1.140 0.0174 -0.0972", + " 8.00 1.193 0.0198 -0.0968", + " 8.50 1.242 0.0231 -0.0958", + " 9.00 1.287 0.0275 -0.0948", + " 9.50 1.333 0.0323 -0.0942", + " 10.00 1.368 0.0393 -0.0926", + " 10.50 1.400 0.0475 -0.0908", + " 11.00 1.425 0.0580 -0.0890", + " 11.50 1.449 0.0691 -0.0877", + " 12.00 1.473 0.0816 -0.0870", + " 12.50 1.494 0.0973 -0.0870", + " 13.00 1.513 0.1129 -0.0876", + " 13.50 1.538 0.1288 -0.0886", + " 14.50 1.587 0.1650 -0.0917", + " 15.00 1.614 0.1845 -0.0939", + " 15.50 1.631 0.2052 -0.0966", + " 16.00 1.649 0.2250 -0.0996", + " 16.50 1.666 0.2467 -0.1031", + " 17.00 1.681 0.2684 -0.1069", + " 17.50 1.699 0.2900 -0.1110", + " 18.00 1.719 0.3121 -0.1157", + " 19.00 1.751 0.3554 -0.1242", + " 19.50 1.767 0.3783 -0.1291", + " 20.50 1.798 0.4212 -0.1384", + " 21.00 1.810 0.4415 -0.1416", + " 22.00 1.830 0.4830 -0.1479", + " 23.00 1.847 0.5257 -0.1542", + " 24.00 1.861 0.5694 -0.1603", + " 25.00 1.872 0.6141 -0.1664", + " 26.00 1.881 0.6593 -0.1724", + " 28.00 1.894 0.7513 -0.1841", + " 30.00 1.904 0.8441 -0.1954", + " 32.00 1.915 0.9364 -0.2063", + " 35.00 1.929 1.0722 -0.2220", + " 40.00 1.903 1.2873 -0.2468", + " 45.00 1.820 1.4796 -0.2701", + " 50.00 1.690 1.6401 -0.2921", + " 55.00 1.522 1.7609 -0.3127", + " 60.00 1.323 1.8360 -0.3321", + " 65.00 1.106 1.8614 -0.3502", + " 70.00 0.880 1.8347 -0.3672", + " 75.00 0.658 1.7567 -0.3830", + " 80.00 0.449 1.6334 -0.3977", + " 85.00 0.267 1.4847 -0.4112", + " 90.00 0.124 1.3879 -0.4234", + " 95.00 0.002 1.3912 -0.4343", + " 100.00 -0.118 1.3795 -0.4437", + " 105.00 -0.235 1.3528 -0.4514", + " 110.00 -0.348 1.3114 -0.4573", + " 115.00 -0.453 1.2557 -0.4610", + " 120.00 -0.549 1.1864 -0.4623", + " 125.00 -0.633 1.1041 -0.4606", + " 130.00 -0.702 1.0102 -0.4554", + " 135.00 -0.754 0.9060 -0.4462", + " 140.00 -0.787 0.7935 -0.4323", + " 145.00 -0.797 0.6750 -0.4127", + " 150.00 -0.782 0.5532 -0.3863", + " 155.00 -0.739 0.4318 -0.3521", + " 160.00 -0.664 0.3147 -0.3085", + " 170.00 -0.410 0.1144 -0.1858", + " 175.00 -0.226 0.0702 -0.1022", + " 180.00 0.000 0.0602 0.0000" + ], + "BL_File": { + "Name": "BL_File", + "Type": "Path", + "Desc": "The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + "Line": 415, + "Value": "FileNotFound", + "FileType": "", + "Root": false + } + }, + { + "Name": "DU35_A17.dat", + "Type": "AirfoilInfo", + "Lines": [ + "! ------------ AirfoilInfo v1.01.x Input File ----------------------------------", + "! DU35 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN).", + "! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls.", + "! note that this file uses Marshall Buhl's new input file processing; start all comment lines with !", + "! ------------------------------------------------------------------------------", + "\"DEFAULT\" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; \"default\"} [default=1]", + " 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)", + " 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included.", + "! ......... x-y coordinates are next if NumCoords \u003e 0 .............", + "! x-y coordinate of airfoil reference", + "! x/c y/c", + "0.25 0", + "! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2\u0026t=440", + "! Adjusted DU 35", + "! x/c y/c", + "1.00000 0.00283", + "0.99660 0.00378", + "0.99314 0.00477", + "0.98961 0.00578", + "0.98601 0.00683", + "0.98235 0.00789", + "0.97863 0.00897", + "0.97484 0.01006", + "0.97098 0.01116", + "0.96706 0.01228", + "0.96307 0.01342", + "0.95902 0.01456", + "0.95490 0.01571", + "0.95072 0.01688", + "0.94647 0.01806", + "0.94216 0.01926", + "0.93778 0.02046", + "0.93333 0.02169", + "0.92882 0.02292", + "0.92425 0.02419", + "0.91961 0.02547", + "0.91490 0.02675", + "0.91013 0.02807", + "0.90529 0.02941", + "0.90039 0.03077", + "0.89542 0.03214", + "0.89039 0.03353", + "0.88529 0.03495", + "0.88013 0.03638", + "0.87490 0.03782", + "0.86961 0.03929", + "0.86425 0.04079", + "0.85882 0.04230", + "0.85333 0.04383", + "0.84778 0.04538", + "0.84216 0.04694", + "0.83647 0.04853", + "0.83072 0.05013", + "0.82490 0.05176", + "0.81902 0.05340", + "0.81307 0.05506", + "0.80706 0.05673", + "0.80098 0.05842", + "0.79484 0.06013", + "0.78863 0.06184", + "0.78235 0.06358", + "0.77601 0.06531", + "0.76961 0.06708", + "0.76314 0.06885", + "0.75660 0.07064", + "0.75000 0.07244", + "0.74333 0.07426", + "0.73667 0.07606", + "0.73000 0.07786", + "0.72333 0.07966", + "0.71667 0.08144", + "0.71000 0.08322", + "0.70333 0.08498", + "0.69667 0.08674", + "0.69000 0.08849", + "0.68333 0.09022", + "0.67667 0.09196", + "0.67000 0.09368", + "0.66333 0.09539", + "0.65667 0.09708", + "0.65000 0.09876", + "0.64333 0.10044", + "0.63667 0.10210", + "0.63000 0.10375", + "0.62333 0.10538", + "0.61667 0.10699", + "0.61000 0.10859", + "0.60333 0.11017", + "0.59667 0.11174", + "0.59000 0.11330", + "0.58333 0.11483", + "0.57667 0.11634", + "0.57000 0.11784", + "0.56333 0.11931", + "0.55667 0.12077", + "0.55000 0.12220", + "0.54333 0.12363", + "0.53667 0.12502", + "0.53000 0.12639", + "0.52333 0.12775", + "0.51667 0.12907", + "0.51000 0.13037", + "0.50333 0.13165", + "0.49667 0.13289", + "0.49000 0.13411", + "0.48333 0.13531", + "0.47667 0.13648", + "0.47000 0.13761", + "0.46333 0.13873", + "0.45667 0.13980", + "0.45000 0.14086", + "0.44333 0.14189", + "0.43667 0.14288", + "0.43000 0.14384", + "0.42333 0.14477", + "0.41667 0.14566", + "0.41000 0.14653", + "0.40333 0.14736", + "0.39667 0.14814", + "0.39000 0.14889", + "0.38333 0.14960", + "0.37667 0.15028", + "0.37000 0.15091", + "0.36333 0.15151", + "0.35667 0.15207", + "0.35000 0.15258", + "0.34333 0.15306", + "0.33667 0.15351", + "0.33000 0.15391", + "0.32333 0.15426", + "0.31667 0.15457", + "0.31000 0.15482", + "0.30333 0.15502", + "0.29667 0.15516", + "0.29000 0.15524", + "0.28333 0.15525", + "0.27667 0.15520", + "0.27000 0.15507", + "0.26333 0.15486", + "0.25667 0.15457", + "0.25000 0.15419", + "0.24342 0.15372", + "0.23693 0.15316", + "0.23053 0.15250", + "0.22421 0.15175", + "0.21798 0.15094", + "0.21184 0.15002", + "0.20579 0.14904", + "0.19982 0.14798", + "0.19395 0.14686", + "0.18816 0.14566", + "0.18245 0.14439", + "0.17684 0.14308", + "0.17131 0.14169", + "0.16587 0.14025", + "0.16052 0.13875", + "0.15526 0.13721", + "0.15008 0.13561", + "0.14499 0.13396", + "0.13999 0.13226", + "0.13508 0.13052", + "0.13026 0.12873", + "0.12552 0.12689", + "0.12087 0.12502", + "0.11631 0.12311", + "0.11183 0.12115", + "0.10745 0.11917", + "0.10315 0.11715", + "0.09893 0.11509", + "0.09481 0.11299", + "0.09077 0.11087", + "0.08683 0.10871", + "0.08297 0.10652", + "0.07919 0.10430", + "0.07551 0.10207", + "0.07191 0.09979", + "0.06840 0.09750", + "0.06498 0.09517", + "0.06164 0.09284", + "0.05840 0.09048", + "0.05524 0.08809", + "0.05217 0.08569", + "0.04918 0.08327", + "0.04629 0.08084", + "0.04348 0.07839", + "0.04076 0.07592", + "0.03812 0.07345", + "0.03558 0.07096", + "0.03312 0.06847", + "0.03075 0.06597", + "0.02847 0.06348", + "0.02627 0.06097", + "0.02417 0.05847", + "0.02215 0.05596", + "0.02022 0.05344", + "0.01837 0.05091", + "0.01662 0.04841", + "0.01495 0.04589", + "0.01337 0.04339", + "0.01187 0.04088", + "0.01047 0.03840", + "0.00915 0.03591", + "0.00792 0.03343", + "0.00678 0.03096", + "0.00572 0.02845", + "0.00476 0.02592", + "0.00388 0.02329", + "0.00309 0.02056", + "0.00238 0.01774", + "0.00177 0.01503", + "0.00124 0.01240", + "0.00080 0.00990", + "0.00044 0.00733", + "0.00018 0.00465", + "0.00000 0.00000", + "0.00018 -0.00461", + "0.00044 -0.00726", + "0.00080 -0.00990", + "0.00124 -0.01246", + "0.00177 -0.01509", + "0.00238 -0.01776", + "0.00309 -0.02049", + "0.00388 -0.02317", + "0.00476 -0.02585", + "0.00572 -0.02848", + "0.00678 -0.03112", + "0.00792 -0.03376", + "0.00915 -0.03642", + "0.01047 -0.03911", + "0.01187 -0.04178", + "0.01337 -0.04450", + "0.01495 -0.04721", + "0.01662 -0.04995", + "0.01837 -0.05269", + "0.02022 -0.05547", + "0.02215 -0.05825", + "0.02417 -0.06105", + "0.02627 -0.06386", + "0.02847 -0.06670", + "0.03075 -0.06955", + "0.03312 -0.07244", + "0.03558 -0.07536", + "0.03812 -0.07828", + "0.04076 -0.08125", + "0.04348 -0.08422", + "0.04629 -0.08720", + "0.04918 -0.09020", + "0.05217 -0.09321", + "0.05524 -0.09622", + "0.05840 -0.09925", + "0.06164 -0.10225", + "0.06498 -0.10528", + "0.06840 -0.10829", + "0.07191 -0.11131", + "0.07551 -0.11431", + "0.07919 -0.11730", + "0.08297 -0.12028", + "0.08683 -0.12325", + "0.09077 -0.12619", + "0.09481 -0.12914", + "0.09893 -0.13205", + "0.10315 -0.13494", + "0.10745 -0.13780", + "0.11183 -0.14065", + "0.11631 -0.14345", + "0.12087 -0.14624", + "0.12552 -0.14898", + "0.13026 -0.15169", + "0.13508 -0.15435", + "0.13999 -0.15697", + "0.14499 -0.15954", + "0.15008 -0.16207", + "0.15526 -0.16454", + "0.16052 -0.16696", + "0.16587 -0.16932", + "0.17131 -0.17163", + "0.17684 -0.17387", + "0.18245 -0.17603", + "0.18816 -0.17814", + "0.19395 -0.18015", + "0.19982 -0.18207", + "0.20579 -0.18391", + "0.21184 -0.18564", + "0.21798 -0.18727", + "0.22421 -0.18877", + "0.23053 -0.19015", + "0.23693 -0.19140", + "0.24342 -0.19250", + "0.25000 -0.19343", + "0.25667 -0.19420", + "0.26333 -0.19481", + "0.27000 -0.19525", + "0.27667 -0.19552", + "0.28333 -0.19562", + "0.29000 -0.19556", + "0.29667 -0.19535", + "0.30333 -0.19498", + "0.31000 -0.19448", + "0.31667 -0.19383", + "0.32333 -0.19303", + "0.33000 -0.19211", + "0.33667 -0.19107", + "0.34333 -0.18991", + "0.35000 -0.18864", + "0.35667 -0.18725", + "0.36333 -0.18577", + "0.37000 -0.18418", + "0.37667 -0.18251", + "0.38333 -0.18074", + "0.39000 -0.17889", + "0.39667 -0.17695", + "0.40333 -0.17496", + "0.41000 -0.17288", + "0.41667 -0.17074", + "0.42333 -0.16855", + "0.43000 -0.16631", + "0.43667 -0.16402", + "0.44333 -0.16167", + "0.45000 -0.15929", + "0.45667 -0.15684", + "0.46333 -0.15436", + "0.47000 -0.15185", + "0.47667 -0.14930", + "0.48333 -0.14671", + "0.49000 -0.14410", + "0.49667 -0.14147", + "0.50333 -0.13881", + "0.51000 -0.13613", + "0.51667 -0.13342", + "0.52333 -0.13071", + "0.53000 -0.12797", + "0.53667 -0.12522", + "0.54333 -0.12247", + "0.55000 -0.11970", + "0.55667 -0.11692", + "0.56333 -0.11413", + "0.57000 -0.11133", + "0.57667 -0.10853", + "0.58333 -0.10573", + "0.59000 -0.10293", + "0.59667 -0.10014", + "0.60333 -0.09734", + "0.61000 -0.09456", + "0.61667 -0.09178", + "0.62333 -0.08901", + "0.63000 -0.08624", + "0.63667 -0.08348", + "0.64333 -0.08074", + "0.65000 -0.07801", + "0.65667 -0.07529", + "0.66333 -0.07257", + "0.67000 -0.06987", + "0.67667 -0.06719", + "0.68333 -0.06452", + "0.69000 -0.06186", + "0.69667 -0.05922", + "0.70333 -0.05661", + "0.71000 -0.05401", + "0.71667 -0.05144", + "0.72333 -0.04889", + "0.73000 -0.04637", + "0.73667 -0.04386", + "0.74333 -0.04140", + "0.75000 -0.03896", + "0.75660 -0.03658", + "0.76314 -0.03425", + "0.76961 -0.03199", + "0.77601 -0.02979", + "0.78235 -0.02765", + "0.78863 -0.02557", + "0.79484 -0.02357", + "0.80098 -0.02162", + "0.80706 -0.01974", + "0.81307 -0.01794", + "0.81902 -0.01621", + "0.82490 -0.01454", + "0.83072 -0.01294", + "0.83647 -0.01142", + "0.84216 -0.00996", + "0.84778 -0.00858", + "0.85333 -0.00727", + "0.85882 -0.00604", + "0.86425 -0.00487", + "0.86961 -0.00377", + "0.87490 -0.00276", + "0.88013 -0.00182", + "0.88529 -0.00095", + "0.89039 -0.00014", + "0.89542 0.00061", + "0.90039 0.00128", + "0.90529 0.00189", + "0.91013 0.00243", + "0.91490 0.00293", + "0.91961 0.00335", + "0.92425 0.00370", + "0.92882 0.00401", + "0.93333 0.00425", + "0.93778 0.00441", + "0.94216 0.00452", + "0.94647 0.00455", + "0.95072 0.00451", + "0.95490 0.00439", + "0.95902 0.00420", + "0.96307 0.00394", + "0.96706 0.00358", + "0.97098 0.00315", + "0.97484 0.00264", + "0.97863 0.00206", + "0.98235 0.00141", + "0.98601 0.00069", + "0.98961 -0.00011", + "0.99314 -0.00097", + "0.99660 -0.00190", + "1.00000 -0.00283", + "\"unused\" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + " 1 NumTabs ! Number of airfoil tables in this file.", + "! ------------------------------------------------------------------------------", + "! data for table 1", + "! ------------------------------------------------------------------------------", + " 0.75 Re ! Reynolds number in millions", + " 0 UserProp ! User property (control) setting", + "True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line", + "!........................................", + " -1.2 alpha0 ! 0-lift angle of attack, depends on airfoil.", + " 11.5 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003ealpha0. (deg)", + " -11.5 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003calpha0. (deg)", + " 1 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)", + " 7.1838 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)", + " 3 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]", + " 6 T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on Re,M, and airfoil class. [default = 6]", + " 1.7 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]", + " 11 T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]", + " 0.14 b1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.14]", + " 0.53 b2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.53]", + " 5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]", + " 0.3 A1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.3]", + " 0.7 A2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.7]", + " 1 A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]", + " 0 S1 ! Constant in the f curve best-fit for alpha0\u003c=AOA\u003c=alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S2 ! Constant in the f curve best-fit for AOA\u003e alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S3 ! Constant in the f curve best-fit for alpha2\u003c=AOA\u003c alpha0; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S4 ! Constant in the f curve best-fit for AOA\u003c alpha2; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 1.6717 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.", + " -0.3075 Cn2 ! As Cn1 for negative AOAs.", + " 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19]", + " 0.012 Cd0 ! 2D drag coefficient value at 0-lift.", + " -0.07 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0]", + " 0 k0 ! Constant in the \\hat(x)_cp curve best-fit; = (\\hat(x)_AC-0.25). [ignored if UAMod\u003c\u003e1]", + " 0 k1 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k2 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k3 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod\u003c\u003e1]", + " 0.2 x_cp_bar ! Constant in the expression of \\hat(x)_cp^v. [ignored if UAMod\u003c\u003e1, default = 0.2]", + "\"DEFAULT\" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string \"Default\" sets UACutout to 45 degrees]", + "\"DEFAULT\" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5]", + "!........................................", + "! Table of aerodynamics coefficients", + " 135 NumAlf ! Number of data lines in the following table", + "! Alpha Cl Cd Cm", + "! (deg) (-) (-) (-)", + " -180.00 0.000 0.0407 0.0000", + " -175.00 0.223 0.0507 0.0937", + " -170.00 0.405 0.1055 0.1702", + " -160.00 0.658 0.2982 0.2819", + " -155.00 0.733 0.4121 0.3213", + " -150.00 0.778 0.5308 0.3520", + " -145.00 0.795 0.6503 0.3754", + " -140.00 0.787 0.7672 0.3926", + " -135.00 0.757 0.8785 0.4046", + " -130.00 0.708 0.9819 0.4121", + " -125.00 0.641 1.0756 0.4160", + " -120.00 0.560 1.1580 0.4167", + " -115.00 0.467 1.2280 0.4146", + " -110.00 0.365 1.2847 0.4104", + " -105.00 0.255 1.3274 0.4041", + " -100.00 0.139 1.3557 0.3961", + " -95.00 0.021 1.3692 0.3867", + " -90.00 -0.098 1.3680 0.3759", + " -85.00 -0.216 1.3521 0.3639", + " -80.00 -0.331 1.3218 0.3508", + " -75.00 -0.441 1.2773 0.3367", + " -70.00 -0.544 1.2193 0.3216", + " -65.00 -0.638 1.1486 0.3054", + " -60.00 -0.720 1.0660 0.2884", + " -55.00 -0.788 0.9728 0.2703", + " -50.00 -0.840 0.8705 0.2512", + " -45.00 -0.875 0.7611 0.2311", + " -40.00 -0.889 0.6466 0.2099", + " -35.00 -0.880 0.5299 0.1876", + " -30.00 -0.846 0.4141 0.1641", + " -25.00 -0.784 0.3030 0.1396", + " -24.00 -0.768 0.2817 0.1345", + " -23.00 -0.751 0.2608 0.1294", + " -22.00 -0.733 0.2404 0.1243", + " -21.00 -0.714 0.2205 0.1191", + " -20.00 -0.693 0.2011 0.1139", + " -19.00 -0.671 0.1822 0.1086", + " -18.00 -0.648 0.1640 0.1032", + " -17.00 -0.624 0.1465 0.0975", + " -16.00 -0.601 0.1300 0.0898", + " -15.00 -0.579 0.1145 0.0799", + " -14.00 -0.559 0.1000 0.0682", + " -13.00 -0.539 0.0867 0.0547", + " -12.00 -0.519 0.0744 0.0397", + " -11.00 -0.499 0.0633 0.0234", + " -10.00 -0.480 0.0534 0.0060", + " -5.54 -0.385 0.0245 -0.0800", + " -5.04 -0.359 0.0225 -0.0800", + " -4.54 -0.360 0.0196 -0.0800", + " -4.04 -0.355 0.0174 -0.0800", + " -3.54 -0.307 0.0162 -0.0800", + " -3.04 -0.246 0.0144 -0.0800", + " -3.00 -0.240 0.0240 -0.0623", + " -2.50 -0.163 0.0188 -0.0674", + " -2.00 -0.091 0.0160 -0.0712", + " -1.50 -0.019 0.0137 -0.0746", + " -1.00 0.052 0.0118 -0.0778", + " -0.50 0.121 0.0104 -0.0806", + " 0.00 0.196 0.0094 -0.0831", + " 0.50 0.265 0.0096 -0.0863", + " 1.00 0.335 0.0098 -0.0895", + " 1.50 0.404 0.0099 -0.0924", + " 2.00 0.472 0.0100 -0.0949", + " 2.50 0.540 0.0102 -0.0973", + " 3.00 0.608 0.0103 -0.0996", + " 3.50 0.674 0.0104 -0.1016", + " 4.00 0.742 0.0105 -0.1037", + " 4.50 0.809 0.0107 -0.1057", + " 5.00 0.875 0.0108 -0.1076", + " 5.50 0.941 0.0109 -0.1094", + " 6.00 1.007 0.0110 -0.1109", + " 6.50 1.071 0.0113 -0.1118", + " 7.00 1.134 0.0115 -0.1127", + " 7.50 1.198 0.0117 -0.1138", + " 8.00 1.260 0.0120 -0.1144", + " 8.50 1.318 0.0126 -0.1137", + " 9.00 1.368 0.0133 -0.1112", + " 9.50 1.422 0.0143 -0.1100", + " 10.00 1.475 0.0156 -0.1086", + " 10.50 1.523 0.0174 -0.1064", + " 11.00 1.570 0.0194 -0.1044", + " 11.50 1.609 0.0227 -0.1013", + " 12.00 1.642 0.0269 -0.0980", + " 12.50 1.675 0.0319 -0.0953", + " 13.00 1.700 0.0398 -0.0925", + " 13.50 1.717 0.0488 -0.0896", + " 14.00 1.712 0.0614 -0.0864", + " 14.50 1.703 0.0786 -0.0840", + " 15.50 1.671 0.1173 -0.0830", + " 16.00 1.649 0.1377 -0.0848", + " 16.50 1.621 0.1600 -0.0880", + " 17.00 1.598 0.1814 -0.0926", + " 17.50 1.571 0.2042 -0.0984", + " 18.00 1.549 0.2316 -0.1052", + " 19.00 1.544 0.2719 -0.1158", + " 19.50 1.549 0.2906 -0.1213", + " 20.00 1.565 0.3085 -0.1248", + " 21.00 1.565 0.3447 -0.1317", + " 22.00 1.563 0.3820 -0.1385", + " 23.00 1.558 0.4203 -0.1452", + " 24.00 1.552 0.4593 -0.1518", + " 25.00 1.546 0.4988 -0.1583", + " 26.00 1.539 0.5387 -0.1647", + " 28.00 1.527 0.6187 -0.1770", + " 30.00 1.522 0.6978 -0.1886", + " 32.00 1.529 0.7747 -0.1994", + " 35.00 1.544 0.8869 -0.2148", + " 40.00 1.529 1.0671 -0.2392", + " 45.00 1.471 1.2319 -0.2622", + " 50.00 1.376 1.3747 -0.2839", + " 55.00 1.249 1.4899 -0.3043", + " 60.00 1.097 1.5728 -0.3236", + " 65.00 0.928 1.6202 -0.3417", + " 70.00 0.750 1.6302 -0.3586", + " 75.00 0.570 1.6031 -0.3745", + " 80.00 0.396 1.5423 -0.3892", + " 85.00 0.237 1.4598 -0.4028", + " 90.00 0.101 1.4041 -0.4151", + " 95.00 -0.022 1.4053 -0.4261", + " 100.00 -0.143 1.3914 -0.4357", + " 105.00 -0.261 1.3625 -0.4437", + " 110.00 -0.374 1.3188 -0.4498", + " 115.00 -0.480 1.2608 -0.4538", + " 120.00 -0.575 1.1891 -0.4553", + " 125.00 -0.659 1.1046 -0.4540", + " 130.00 -0.727 1.0086 -0.4492", + " 135.00 -0.778 0.9025 -0.4405", + " 140.00 -0.809 0.7883 -0.4270", + " 145.00 -0.818 0.6684 -0.4078", + " 150.00 -0.800 0.5457 -0.3821", + " 155.00 -0.754 0.4236 -0.3484", + " 160.00 -0.677 0.3066 -0.3054", + " 170.00 -0.417 0.1085 -0.1842", + " 175.00 -0.229 0.0510 -0.1013", + " 180.00 0.000 0.0407 0.0000" + ], + "BL_File": { + "Name": "BL_File", + "Type": "Path", + "Desc": "The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + "Line": 415, + "Value": "FileNotFound", + "FileType": "", + "Root": false + } + }, + { + "Name": "DU30_A17.dat", + "Type": "AirfoilInfo", + "Lines": [ + "! ------------ AirfoilInfo v1.01.x Input File ----------------------------------", + "! DU30 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN).", + "! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls.", + "! note that this file uses Marshall Buhl's new input file processing; start all comment lines with !", + "! ------------------------------------------------------------------------------", + "\"DEFAULT\" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; \"default\"} [default=1]", + " 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)", + " 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included.", + "! ......... x-y coordinates are next if NumCoords \u003e 0 .............", + "! x-y coordinate of airfoil reference", + "! x/c y/c", + "0.25 0", + "! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2\u0026t=440", + "! DU 97-W-300.lm", + "! x/c y/c", + "1.00000 0.00246", + "0.99660 0.00340", + "0.99314 0.00437", + "0.98961 0.00536", + "0.98601 0.00638", + "0.98235 0.00740", + "0.97863 0.00843", + "0.97484 0.00947", + "0.97098 0.01051", + "0.96706 0.01157", + "0.96307 0.01264", + "0.95902 0.01371", + "0.95490 0.01479", + "0.95072 0.01588", + "0.94647 0.01698", + "0.94216 0.01810", + "0.93778 0.01922", + "0.93333 0.02036", + "0.92882 0.02151", + "0.92425 0.02268", + "0.91961 0.02386", + "0.91490 0.02505", + "0.91013 0.02626", + "0.90529 0.02749", + "0.90039 0.02873", + "0.89542 0.02999", + "0.89039 0.03126", + "0.88529 0.03255", + "0.88013 0.03385", + "0.87490 0.03516", + "0.86961 0.03649", + "0.86425 0.03784", + "0.85882 0.03921", + "0.85333 0.04058", + "0.84778 0.04197", + "0.84216 0.04337", + "0.83647 0.04479", + "0.83072 0.04622", + "0.82490 0.04767", + "0.81902 0.04913", + "0.81307 0.05060", + "0.80706 0.05208", + "0.80098 0.05357", + "0.79484 0.05508", + "0.78863 0.05659", + "0.78235 0.05812", + 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+ "0.29667 -0.16580", + "0.30333 -0.16548", + "0.31000 -0.16503", + "0.31667 -0.16445", + "0.32333 -0.16374", + "0.33000 -0.16291", + "0.33667 -0.16198", + "0.34333 -0.16094", + "0.35000 -0.15980", + "0.35667 -0.15855", + "0.36333 -0.15722", + "0.37000 -0.15580", + "0.37667 -0.15429", + "0.38333 -0.15270", + "0.39000 -0.15104", + "0.39667 -0.14931", + "0.40333 -0.14752", + "0.41000 -0.14566", + "0.41667 -0.14374", + "0.42333 -0.14178", + "0.43000 -0.13977", + "0.43667 -0.13772", + "0.44333 -0.13562", + "0.45000 -0.13348", + "0.45667 -0.13130", + "0.46333 -0.12908", + "0.47000 -0.12683", + "0.47667 -0.12456", + "0.48333 -0.12225", + "0.49000 -0.11992", + "0.49667 -0.11757", + "0.50333 -0.11520", + "0.51000 -0.11281", + "0.51667 -0.11040", + "0.52333 -0.10799", + "0.53000 -0.10555", + "0.53667 -0.10310", + "0.54333 -0.10065", + "0.55000 -0.09818", + "0.55667 -0.09570", + "0.56333 -0.09321", + "0.57000 -0.09071", + "0.57667 -0.08821", + "0.58333 -0.08571", + "0.59000 -0.08320", + "0.59667 -0.08070", + "0.60333 -0.07819", + "0.61000 -0.07569", + "0.61667 -0.07319", + "0.62333 -0.07070", + "0.63000 -0.06820", + "0.63667 -0.06572", + "0.64333 -0.06325", + "0.65000 -0.06079", + "0.65667 -0.05834", + "0.66333 -0.05590", + "0.67000 -0.05347", + "0.67667 -0.05106", + "0.68333 -0.04867", + "0.69000 -0.04629", + "0.69667 -0.04394", + "0.70333 -0.04161", + "0.71000 -0.03931", + "0.71667 -0.03703", + "0.72333 -0.03478", + "0.73000 -0.03256", + "0.73667 -0.03037", + "0.74333 -0.02822", + "0.75000 -0.02610", + "0.75660 -0.02405", + "0.76314 -0.02205", + "0.76961 -0.02013", + "0.77601 -0.01827", + "0.78235 -0.01647", + "0.78863 -0.01474", + "0.79484 -0.01309", + "0.80098 -0.01150", + "0.80706 -0.00998", + "0.81307 -0.00854", + "0.81902 -0.00717", + "0.82490 -0.00586", + "0.83072 -0.00462", + "0.83647 -0.00346", + "0.84216 -0.00236", + "0.84778 -0.00133", + "0.85333 -0.00037", + "0.85882 0.00052", + "0.86425 0.00134", + "0.86961 0.00210", + "0.87490 0.00278", + "0.88013 0.00340", + "0.88529 0.00395", + "0.89039 0.00444", + "0.89542 0.00487", + "0.90039 0.00524", + "0.90529 0.00555", + "0.91013 0.00580", + "0.91490 0.00600", + "0.91961 0.00614", + "0.92425 0.00622", + "0.92882 0.00625", + "0.93333 0.00623", + "0.93778 0.00615", + "0.94216 0.00602", + "0.94647 0.00583", + "0.95072 0.00558", + "0.95490 0.00528", + "0.95902 0.00493", + "0.96307 0.00452", + "0.96706 0.00405", + "0.97098 0.00352", + "0.97484 0.00294", + "0.97863 0.00231", + "0.98235 0.00163", + "0.98601 0.00090", + "0.98961 0.00012", + "0.99314 -0.00071", + "0.99660 -0.00158", + "1.00000 -0.00246", + "\"unused\" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + " 1 NumTabs ! Number of airfoil tables in this file.", + "! ------------------------------------------------------------------------------", + "! data for table 1", + "! ------------------------------------------------------------------------------", + " 0.75 Re ! Reynolds number in millions", + " 0 UserProp ! User property (control) setting", + "True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line", + "!........................................", + " -2.2 alpha0 ! 0-lift angle of attack, depends on airfoil.", + " 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003ealpha0. (deg)", + " -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003calpha0. (deg)", + " 1 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)", + " 7.3326 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)", + " 3 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]", + " 6 T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on Re,M, and airfoil class. [default = 6]", + " 1.7 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]", + " 11 T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]", + " 0.14 b1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.14]", + " 0.53 b2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.53]", + " 5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]", + " 0.3 A1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.3]", + " 0.7 A2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.7]", + " 1 A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]", + " 0 S1 ! Constant in the f curve best-fit for alpha0\u003c=AOA\u003c=alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S2 ! Constant in the f curve best-fit for AOA\u003e alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S3 ! Constant in the f curve best-fit for alpha2\u003c=AOA\u003c alpha0; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S4 ! Constant in the f curve best-fit for AOA\u003c alpha2; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 1.449 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.", + " -0.6138 Cn2 ! As Cn1 for negative AOAs.", + " 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19]", + " 0.008 Cd0 ! 2D drag coefficient value at 0-lift.", + " -0.09 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0]", + " 0 k0 ! Constant in the \\hat(x)_cp curve best-fit; = (\\hat(x)_AC-0.25). [ignored if UAMod\u003c\u003e1]", + " 0 k1 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k2 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k3 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod\u003c\u003e1]", + " 0.2 x_cp_bar ! Constant in the expression of \\hat(x)_cp^v. [ignored if UAMod\u003c\u003e1, default = 0.2]", + "\"DEFAULT\" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string \"Default\" sets UACutout to 45 degrees]", + "\"DEFAULT\" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5]", + "!........................................", + "! Table of aerodynamics coefficients", + " 143 NumAlf ! Number of data lines in the following table", + "! Alpha Cl Cd Cm", + "! (deg) (-) (-) (-)", + " -180.00 0.000 0.0267 0.0000", + " -175.00 0.274 0.0370 0.1379", + " -170.00 0.547 0.0968 0.2778", + " -160.00 0.685 0.2876 0.2740", + " -155.00 0.766 0.4025 0.3118", + " -150.00 0.816 0.5232 0.3411", + " -145.00 0.836 0.6454 0.3631", + " -140.00 0.832 0.7656 0.3791", + " -135.00 0.804 0.8807 0.3899", + " -130.00 0.756 0.9882 0.3965", + " -125.00 0.690 1.0861 0.3994", + " -120.00 0.609 1.1730 0.3992", + " -115.00 0.515 1.2474 0.3964", + " -110.00 0.411 1.3084 0.3915", + " -105.00 0.300 1.3552 0.3846", + " -100.00 0.182 1.3875 0.3761", + " -95.00 0.061 1.4048 0.3663", + " -90.00 -0.061 1.4070 0.3551", + " -85.00 -0.183 1.3941 0.3428", + " -80.00 -0.302 1.3664 0.3295", + " -75.00 -0.416 1.3240 0.3153", + " -70.00 -0.523 1.2676 0.3001", + " -65.00 -0.622 1.1978 0.2841", + " -60.00 -0.708 1.1156 0.2672", + " -55.00 -0.781 1.0220 0.2494", + " -50.00 -0.838 0.9187 0.2308", + " -45.00 -0.877 0.8074 0.2113", + " -40.00 -0.895 0.6904 0.1909", + " -35.00 -0.889 0.5703 0.1696", + " -30.00 -0.858 0.4503 0.1475", + " -25.00 -0.832 0.3357 0.1224", + " -24.00 -0.852 0.3147 0.1156", + " -23.00 -0.882 0.2946 0.1081", + " -22.00 -0.919 0.2752 0.1000", + " -21.00 -0.963 0.2566 0.0914", + " -20.00 -1.013 0.2388 0.0823", + " -19.00 -1.067 0.2218 0.0728", + " -18.00 -1.125 0.2056 0.0631", + " -17.00 -1.185 0.1901 0.0531", + " -16.00 -1.245 0.1754 0.0430", + " -15.25 -1.290 0.1649 0.0353", + " -14.24 -1.229 0.1461 0.0240", + " -13.24 -1.148 0.1263 0.0100", + " -12.22 -1.052 0.1051 -0.0090", + " -11.22 -0.965 0.0886 -0.0230", + " -10.19 -0.867 0.0740 -0.0336", + " -9.70 -0.822 0.0684 -0.0375", + " -9.18 -0.769 0.0605 -0.0440", + " -8.18 -0.756 0.0270 -0.0578", + " -7.19 -0.690 0.0180 -0.0590", + " -6.65 -0.616 0.0166 -0.0633", + " -6.13 -0.542 0.0152 -0.0674", + " -6.00 -0.525 0.0117 -0.0732", + " -5.50 -0.451 0.0105 -0.0766", + " -5.00 -0.382 0.0097 -0.0797", + " -4.50 -0.314 0.0092 -0.0825", + " -4.00 -0.251 0.0091 -0.0853", + " -3.50 -0.189 0.0089 -0.0884", + " -3.00 -0.120 0.0089 -0.0914", + " -2.50 -0.051 0.0088 -0.0942", + " -2.00 0.017 0.0088 -0.0969", + " -1.50 0.085 0.0088 -0.0994", + " -1.00 0.152 0.0088 -0.1018", + " -0.50 0.219 0.0088 -0.1041", + " 0.00 0.288 0.0087 -0.1062", + " 0.50 0.354 0.0087 -0.1086", + " 1.00 0.421 0.0088 -0.1107", + " 1.50 0.487 0.0089 -0.1129", + " 2.00 0.554 0.0090 -0.1149", + " 2.50 0.619 0.0091 -0.1168", + " 3.00 0.685 0.0092 -0.1185", + " 3.50 0.749 0.0093 -0.1201", + " 4.00 0.815 0.0095 -0.1218", + " 4.50 0.879 0.0096 -0.1233", + " 5.00 0.944 0.0097 -0.1248", + " 5.50 1.008 0.0099 -0.1260", + " 6.00 1.072 0.0101 -0.1270", + " 6.50 1.135 0.0103 -0.1280", + " 7.00 1.197 0.0107 -0.1287", + " 7.50 1.256 0.0112 -0.1289", + " 8.00 1.305 0.0125 -0.1270", + " 9.00 1.390 0.0155 -0.1207", + " 9.50 1.424 0.0171 -0.1158", + " 10.00 1.458 0.0192 -0.1116", + " 10.50 1.488 0.0219 -0.1073", + " 11.00 1.512 0.0255 -0.1029", + " 11.50 1.533 0.0307 -0.0983", + " 12.00 1.549 0.0370 -0.0949", + " 12.50 1.558 0.0452 -0.0921", + " 13.00 1.470 0.0630 -0.0899", + " 13.50 1.398 0.0784 -0.0885", + " 14.00 1.354 0.0931 -0.0885", + " 14.50 1.336 0.1081 -0.0902", + " 15.00 1.333 0.1239 -0.0928", + " 15.50 1.326 0.1415 -0.0963", + " 16.00 1.329 0.1592 -0.1006", + " 16.50 1.326 0.1743 -0.1042", + " 17.00 1.321 0.1903 -0.1084", + " 17.50 1.331 0.2044 -0.1125", + " 18.00 1.333 0.2186 -0.1169", + " 18.50 1.340 0.2324 -0.1215", + " 19.00 1.362 0.2455 -0.1263", + " 19.50 1.382 0.2584 -0.1313", + " 20.00 1.398 0.2689 -0.1352", + " 20.50 1.426 0.2814 -0.1406", + " 21.00 1.437 0.2943 -0.1462", + " 22.00 1.418 0.3246 -0.1516", + " 23.00 1.397 0.3557 -0.1570", + " 24.00 1.376 0.3875 -0.1623", + " 25.00 1.354 0.4198 -0.1676", + " 26.00 1.332 0.4524 -0.1728", + " 28.00 1.293 0.5183 -0.1832", + " 30.00 1.265 0.5843 -0.1935", + " 32.00 1.253 0.6492 -0.2039", + " 35.00 1.264 0.7438 -0.2193", + " 40.00 1.258 0.8970 -0.2440", + " 45.00 1.217 1.0402 -0.2672", + " 50.00 1.146 1.1686 -0.2891", + " 55.00 1.049 1.2779 -0.3097", + " 60.00 0.932 1.3647 -0.3290", + " 65.00 0.799 1.4267 -0.3471", + " 70.00 0.657 1.4621 -0.3641", + " 75.00 0.509 1.4708 -0.3799", + " 80.00 0.362 1.4544 -0.3946", + " 85.00 0.221 1.4196 -0.4081", + " 90.00 0.092 1.3938 -0.4204", + " 95.00 -0.030 1.3943 -0.4313", + " 100.00 -0.150 1.3798 -0.4408", + " 105.00 -0.267 1.3504 -0.4486", + " 110.00 -0.379 1.3063 -0.4546", + " 115.00 -0.483 1.2481 -0.4584", + " 120.00 -0.578 1.1763 -0.4597", + " 125.00 -0.660 1.0919 -0.4582", + " 130.00 -0.727 0.9962 -0.4532", + " 135.00 -0.777 0.8906 -0.4441", + " 140.00 -0.807 0.7771 -0.4303", + " 145.00 -0.815 0.6581 -0.4109", + " 150.00 -0.797 0.5364 -0.3848", + " 155.00 -0.750 0.4157 -0.3508", + " 160.00 -0.673 0.3000 -0.3074", + " 170.00 -0.547 0.1051 -0.2786", + " 175.00 -0.274 0.0388 -0.1380", + " 180.00 0.000 0.0267 0.0000", + "" + ], + "BL_File": { + "Name": "BL_File", + "Type": "Path", + "Desc": "The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + "Line": 415, + "Value": "FileNotFound", + "FileType": "", + "Root": false + } + }, + { + "Name": "DU25_A17.dat", + "Type": "AirfoilInfo", + "Lines": [ + "! ------------ AirfoilInfo v1.01.x Input File ----------------------------------", + "! DU25 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN).", + "! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls.", + "! note that this file uses Marshall Buhl's new input file processing; start all comment lines with !", + "! ------------------------------------------------------------------------------", + "\"DEFAULT\" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; \"default\"} [default=1]", + " 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)", + " 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included.", + "! ......... x-y coordinates are next if NumCoords \u003e 0 .............", + "! x-y coordinate of airfoil reference", + "! x/c y/c", + "0.25 0", + "! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2\u0026t=440", + "! DU 91-W2-250.lm", + "! x/c y/c", + "1.00000 0.00213", + "0.99660 0.00314", + "0.99314 0.00414", + "0.98961 0.00515", + "0.98601 0.00617", + "0.98235 0.00720", + "0.97863 0.00822", + "0.97484 0.00926", + "0.97098 0.01030", + "0.96706 0.01135", + "0.96307 0.01240", + "0.95902 0.01347", + "0.95490 0.01454", + "0.95072 0.01562", + "0.94647 0.01672", + "0.94216 0.01783", + "0.93778 0.01895", + "0.93333 0.02009", + "0.92882 0.02125", + "0.92425 0.02241", + "0.91961 0.02359", + "0.91490 0.02479", + "0.91013 0.02600", + "0.90529 0.02722", + "0.90039 0.02846", + "0.89542 0.02972", + "0.89039 0.03099", + "0.88529 0.03227", + "0.88013 0.03357", + "0.87490 0.03489", + "0.86961 0.03622", + "0.86425 0.03756", + "0.85882 0.03892", + "0.85333 0.04029", + "0.84778 0.04167", + "0.84216 0.04306", + "0.83647 0.04447", + "0.83072 0.04589", + "0.82490 0.04732", + "0.81902 0.04877", + "0.81307 0.05023", + "0.80706 0.05170", + "0.80098 0.05319", + "0.79484 0.05468", + "0.78863 0.05619", + "0.78235 0.05771", + 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0.00975", + "0.89039 0.00983", + "0.89542 0.00985", + "0.90039 0.00982", + "0.90529 0.00972", + "0.91013 0.00957", + "0.91490 0.00936", + "0.91961 0.00910", + "0.92425 0.00880", + "0.92882 0.00844", + "0.93333 0.00804", + "0.93778 0.00760", + "0.94216 0.00712", + "0.94647 0.00660", + "0.95072 0.00606", + "0.95490 0.00549", + "0.95902 0.00490", + "0.96307 0.00429", + "0.96706 0.00367", + "0.97098 0.00303", + "0.97484 0.00238", + "0.97863 0.00173", + "0.98235 0.00108", + "0.98601 0.00043", + "0.98961 -0.00022", + "0.99314 -0.00086", + "0.99660 -0.00149", + "1.00000 -0.00213", + "\"unused\" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + " 1 NumTabs ! Number of airfoil tables in this file.", + "! ------------------------------------------------------------------------------", + "! data for table 1", + "! ------------------------------------------------------------------------------", + " 0.75 Re ! Reynolds number in millions", + " 0 UserProp ! User property (control) setting", + "True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line", + "!........................................", + " -3.2 alpha0 ! 0-lift angle of attack, depends on airfoil.", + " 8.5 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003ealpha0. (deg)", + " -8.5 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003calpha0. (deg)", + " 1 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)", + " 6.4462 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)", + " 3 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]", + " 6 T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on Re,M, and airfoil class. [default = 6]", + " 1.7 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]", + " 11 T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]", + " 0.14 b1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.14]", + " 0.53 b2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.53]", + " 5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]", + " 0.3 A1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.3]", + " 0.7 A2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.7]", + " 1 A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]", + " 0 S1 ! Constant in the f curve best-fit for alpha0\u003c=AOA\u003c=alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S2 ! Constant in the f curve best-fit for AOA\u003e alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S3 ! Constant in the f curve best-fit for alpha2\u003c=AOA\u003c alpha0; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S4 ! Constant in the f curve best-fit for AOA\u003c alpha2; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 1.4336 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.", + " -0.6873 Cn2 ! As Cn1 for negative AOAs.", + " 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19]", + " 0.006 Cd0 ! 2D drag coefficient value at 0-lift.", + " -0.12 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0]", + " 0 k0 ! Constant in the \\hat(x)_cp curve best-fit; = (\\hat(x)_AC-0.25). [ignored if UAMod\u003c\u003e1]", + " 0 k1 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k2 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k3 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod\u003c\u003e1]", + " 0.2 x_cp_bar ! Constant in the expression of \\hat(x)_cp^v. [ignored if UAMod\u003c\u003e1, default = 0.2]", + "\"DEFAULT\" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string \"Default\" sets UACutout to 45 degrees]", + "\"DEFAULT\" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5]", + "!........................................", + "! Table of aerodynamics coefficients", + " 140 NumAlf ! Number of data lines in the following table", + "! Alpha Cl Cd Cm", + "! (deg) (-) (-) (-)", + " -180.00 0.000 0.0202 0.0000", + " -175.00 0.368 0.0324 0.1845", + " -170.00 0.735 0.0943 0.3701", + " -160.00 0.695 0.2848 0.2679", + " -155.00 0.777 0.4001 0.3046", + " -150.00 0.828 0.5215 0.3329", + " -145.00 0.850 0.6447 0.3540", + " -140.00 0.846 0.7660 0.3693", + " -135.00 0.818 0.8823 0.3794", + " -130.00 0.771 0.9911 0.3854", + " -125.00 0.705 1.0905 0.3878", + " -120.00 0.624 1.1787 0.3872", + " -115.00 0.530 1.2545 0.3841", + " -110.00 0.426 1.3168 0.3788", + " -105.00 0.314 1.3650 0.3716", + " -100.00 0.195 1.3984 0.3629", + " -95.00 0.073 1.4169 0.3529", + " -90.00 -0.050 1.4201 0.3416", + " -85.00 -0.173 1.4081 0.3292", + " -80.00 -0.294 1.3811 0.3159", + " -75.00 -0.409 1.3394 0.3017", + " -70.00 -0.518 1.2833 0.2866", + " -65.00 -0.617 1.2138 0.2707", + " -60.00 -0.706 1.1315 0.2539", + " -55.00 -0.780 1.0378 0.2364", + " -50.00 -0.839 0.9341 0.2181", + " -45.00 -0.879 0.8221 0.1991", + " -40.00 -0.898 0.7042 0.1792", + " -35.00 -0.893 0.5829 0.1587", + " -30.00 -0.862 0.4616 0.1374", + " -25.00 -0.803 0.3441 0.1154", + " -24.00 -0.792 0.3209 0.1101", + " -23.00 -0.789 0.2972 0.1031", + " -22.00 -0.792 0.2730 0.0947", + " -21.00 -0.801 0.2485 0.0849", + " -20.00 -0.815 0.2237 0.0739", + " -19.00 -0.833 0.1990 0.0618", + " -18.00 -0.854 0.1743 0.0488", + " -17.00 -0.879 0.1498 0.0351", + " -16.00 -0.905 0.1256 0.0208", + " -15.00 -0.932 0.1020 0.0060", + " -14.00 -0.959 0.0789 -0.0091", + " -13.00 -0.985 0.0567 -0.0243", + " -12.01 -0.953 0.0271 -0.0349", + " -11.00 -0.900 0.0303 -0.0361", + " -9.98 -0.827 0.0287 -0.0464", + " -8.98 -0.753 0.0271 -0.0534", + " -8.47 -0.691 0.0264 -0.0650", + " -7.45 -0.555 0.0114 -0.0782", + " -6.42 -0.413 0.0094 -0.0904", + " -5.40 -0.271 0.0086 -0.1006", + " -5.00 -0.220 0.0073 -0.1107", + " -4.50 -0.152 0.0071 -0.1135", + " -4.00 -0.084 0.0070 -0.1162", + " -3.50 -0.018 0.0069 -0.1186", + " -3.00 0.049 0.0068 -0.1209", + " -2.50 0.115 0.0068 -0.1231", + " -2.00 0.181 0.0068 -0.1252", + " -1.50 0.247 0.0067 -0.1272", + " -1.00 0.312 0.0067 -0.1293", + " -0.50 0.377 0.0067 -0.1311", + " 0.00 0.444 0.0065 -0.1330", + " 0.50 0.508 0.0065 -0.1347", + " 1.00 0.573 0.0066 -0.1364", + " 1.50 0.636 0.0067 -0.1380", + " 2.00 0.701 0.0068 -0.1396", + " 2.50 0.765 0.0069 -0.1411", + " 3.00 0.827 0.0070 -0.1424", + " 3.50 0.890 0.0071 -0.1437", + " 4.00 0.952 0.0073 -0.1448", + " 4.50 1.013 0.0076 -0.1456", + " 5.00 1.062 0.0079 -0.1445", + " 6.00 1.161 0.0099 -0.1419", + " 6.50 1.208 0.0117 -0.1403", + " 7.00 1.254 0.0132 -0.1382", + " 7.50 1.301 0.0143 -0.1362", + " 8.00 1.336 0.0153 -0.1320", + " 8.50 1.369 0.0165 -0.1276", + " 9.00 1.400 0.0181 -0.1234", + " 9.50 1.428 0.0211 -0.1193", + " 10.00 1.442 0.0262 -0.1152", + " 10.50 1.427 0.0336 -0.1115", + " 11.00 1.374 0.0420 -0.1081", + " 11.50 1.316 0.0515 -0.1052", + " 12.00 1.277 0.0601 -0.1026", + " 12.50 1.250 0.0693 -0.1000", + " 13.00 1.246 0.0785 -0.0980", + " 13.50 1.247 0.0888 -0.0969", + " 14.00 1.256 0.1000 -0.0968", + " 14.50 1.260 0.1108 -0.0973", + " 15.00 1.271 0.1219 -0.0981", + " 15.50 1.281 0.1325 -0.0992", + " 16.00 1.289 0.1433 -0.1006", + " 16.50 1.294 0.1541 -0.1023", + " 17.00 1.304 0.1649 -0.1042", + " 17.50 1.309 0.1754 -0.1064", + " 18.00 1.315 0.1845 -0.1082", + " 18.50 1.320 0.1953 -0.1110", + " 19.00 1.330 0.2061 -0.1143", + " 19.50 1.343 0.2170 -0.1179", + " 20.00 1.354 0.2280 -0.1219", + " 20.50 1.359 0.2390 -0.1261", + " 21.00 1.360 0.2536 -0.1303", + " 22.00 1.325 0.2814 -0.1375", + " 23.00 1.288 0.3098 -0.1446", + " 24.00 1.251 0.3386 -0.1515", + " 25.00 1.215 0.3678 -0.1584", + " 26.00 1.181 0.3972 -0.1651", + " 28.00 1.120 0.4563 -0.1781", + " 30.00 1.076 0.5149 -0.1904", + " 32.00 1.056 0.5720 -0.2017", + " 35.00 1.066 0.6548 -0.2173", + " 40.00 1.064 0.7901 -0.2418", + " 45.00 1.035 0.9190 -0.2650", + " 50.00 0.980 1.0378 -0.2867", + " 55.00 0.904 1.1434 -0.3072", + " 60.00 0.810 1.2333 -0.3265", + " 65.00 0.702 1.3055 -0.3446", + " 70.00 0.582 1.3587 -0.3616", + " 75.00 0.456 1.3922 -0.3775", + " 80.00 0.326 1.4063 -0.3921", + " 85.00 0.197 1.4042 -0.4057", + " 90.00 0.072 1.3985 -0.4180", + " 95.00 -0.050 1.3973 -0.4289", + " 100.00 -0.170 1.3810 -0.4385", + " 105.00 -0.287 1.3498 -0.4464", + " 110.00 -0.399 1.3041 -0.4524", + " 115.00 -0.502 1.2442 -0.4563", + " 120.00 -0.596 1.1709 -0.4577", + " 125.00 -0.677 1.0852 -0.4563", + " 130.00 -0.743 0.9883 -0.4514", + " 135.00 -0.792 0.8818 -0.4425", + " 140.00 -0.821 0.7676 -0.4288", + " 145.00 -0.826 0.6481 -0.4095", + " 150.00 -0.806 0.5264 -0.3836", + " 155.00 -0.758 0.4060 -0.3497", + " 160.00 -0.679 0.2912 -0.3065", + " 170.00 -0.735 0.0995 -0.3706", + " 175.00 -0.368 0.0356 -0.1846", + " 180.00 0.000 0.0202 0.0000" + ], + "BL_File": { + "Name": "BL_File", + "Type": "Path", + "Desc": "The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + "Line": 415, + "Value": "FileNotFound", + "FileType": "", + "Root": false + } + }, + { + "Name": "DU21_A17.dat", + "Type": "AirfoilInfo", + "Lines": [ + "! ------------ AirfoilInfo v1.01.x Input File ----------------------------------", + "! DU21 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN).", + "! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls.", + "! note that this file uses Marshall Buhl's new input file processing; start all comment lines with !", + "! ------------------------------------------------------------------------------", + "\"DEFAULT\" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; \"default\"} [default=1]", + " 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)", + " 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included.", + "! ......... x-y coordinates are next if NumCoords \u003e 0 .............", + "! x-y coordinate of airfoil reference", + "! x/c y/c", + "0.25 0", + "! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2\u0026t=440", + "! DU 93-W-210.lm", + "! x/c y/c", + "1.00000 0.00194", + "0.99660 0.00304", + "0.99314 0.00411", + "0.98961 0.00516", + "0.98601 0.00618", + "0.98235 0.00720", + "0.97863 0.00823", + "0.97484 0.00927", + "0.97098 0.01033", + "0.96706 0.01139", + "0.96307 0.01246", + "0.95902 0.01354", + "0.95490 0.01463", + "0.95072 0.01573", + "0.94647 0.01684", + "0.94216 0.01797", + "0.93778 0.01911", + "0.93333 0.02026", + "0.92882 0.02142", + "0.92425 0.02260", + "0.91961 0.02379", + "0.91490 0.02499", + "0.91013 0.02621", + "0.90529 0.02744", + "0.90039 0.02869", + "0.89542 0.02995", + "0.89039 0.03122", + "0.88529 0.03250", + "0.88013 0.03379", + "0.87490 0.03510", + "0.86961 0.03643", + "0.86425 0.03776", + "0.85882 0.03912", + "0.85333 0.04048", + "0.84778 0.04186", + "0.84216 0.04326", + "0.83647 0.04466", + "0.83072 0.04608", + "0.82490 0.04752", + "0.81902 0.04896", + "0.81307 0.05041", + "0.80706 0.05188", + "0.80098 0.05336", + "0.79484 0.05484", + "0.78863 0.05634", + "0.78235 0.05784", + 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+ "0.29667 -0.08693", + "0.30333 -0.08692", + "0.31000 -0.08686", + "0.31667 -0.08676", + "0.32333 -0.08660", + "0.33000 -0.08640", + "0.33667 -0.08615", + "0.34333 -0.08586", + "0.35000 -0.08553", + "0.35667 -0.08515", + "0.36333 -0.08473", + "0.37000 -0.08427", + "0.37667 -0.08376", + "0.38333 -0.08322", + "0.39000 -0.08263", + "0.39667 -0.08200", + "0.40333 -0.08134", + "0.41000 -0.08062", + "0.41667 -0.07987", + "0.42333 -0.07908", + "0.43000 -0.07824", + "0.43667 -0.07736", + "0.44333 -0.07644", + "0.45000 -0.07548", + "0.45667 -0.07448", + "0.46333 -0.07343", + "0.47000 -0.07235", + "0.47667 -0.07122", + "0.48333 -0.07006", + "0.49000 -0.06886", + "0.49667 -0.06763", + "0.50333 -0.06636", + "0.51000 -0.06506", + "0.51667 -0.06373", + "0.52333 -0.06237", + "0.53000 -0.06097", + "0.53667 -0.05955", + "0.54333 -0.05810", + "0.55000 -0.05663", + "0.55667 -0.05513", + "0.56333 -0.05361", + "0.57000 -0.05207", + "0.57667 -0.05050", + "0.58333 -0.04892", + "0.59000 -0.04732", + "0.59667 -0.04571", + "0.60333 -0.04408", + "0.61000 -0.04243", + "0.61667 -0.04078", + "0.62333 -0.03911", + "0.63000 -0.03744", + "0.63667 -0.03576", + "0.64333 -0.03409", + "0.65000 -0.03241", + "0.65667 -0.03073", + "0.66333 -0.02906", + "0.67000 -0.02740", + "0.67667 -0.02574", + "0.68333 -0.02411", + "0.69000 -0.02248", + "0.69667 -0.02088", + "0.70333 -0.01930", + "0.71000 -0.01774", + "0.71667 -0.01620", + "0.72333 -0.01470", + "0.73000 -0.01323", + "0.73667 -0.01179", + "0.74333 -0.01039", + "0.75000 -0.00903", + "0.75660 -0.00772", + "0.76314 -0.00647", + "0.76961 -0.00528", + "0.77601 -0.00416", + "0.78235 -0.00308", + "0.78863 -0.00207", + "0.79484 -0.00112", + "0.80098 -0.00023", + "0.80706 0.00060", + "0.81307 0.00136", + "0.81902 0.00207", + "0.82490 0.00273", + "0.83072 0.00333", + "0.83647 0.00387", + "0.84216 0.00435", + "0.84778 0.00479", + "0.85333 0.00517", + "0.85882 0.00550", + "0.86425 0.00578", + "0.86961 0.00601", + "0.87490 0.00620", + "0.88013 0.00633", + "0.88529 0.00643", + "0.89039 0.00648", + "0.89542 0.00649", + "0.90039 0.00646", + "0.90529 0.00639", + "0.91013 0.00628", + "0.91490 0.00613", + "0.91961 0.00595", + "0.92425 0.00574", + "0.92882 0.00550", + "0.93333 0.00523", + "0.93778 0.00494", + "0.94216 0.00462", + "0.94647 0.00428", + "0.95072 0.00392", + "0.95490 0.00355", + "0.95902 0.00315", + "0.96307 0.00275", + "0.96706 0.00233", + "0.97098 0.00189", + "0.97484 0.00145", + "0.97863 0.00099", + "0.98235 0.00053", + "0.98601 0.00005", + "0.98961 -0.00044", + "0.99314 -0.00094", + "0.99660 -0.00143", + "1.00000 -0.00194", + "\"unused\" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + " 1 NumTabs ! Number of airfoil tables in this file.", + "! ------------------------------------------------------------------------------", + "! data for table 1", + "! ------------------------------------------------------------------------------", + " 0.75 Re ! Reynolds number in millions", + " 0 UserProp ! User property (control) setting", + "True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line", + "!........................................", + " -4.2 alpha0 ! 0-lift angle of attack, depends on airfoil.", + " 8 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003ealpha0. (deg)", + " -8 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003calpha0. (deg)", + " 1 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)", + " 6.2047 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)", + " 3 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]", + " 6 T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on Re,M, and airfoil class. [default = 6]", + " 1.7 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]", + " 11 T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]", + " 0.14 b1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.14]", + " 0.53 b2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.53]", + " 5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]", + " 0.3 A1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.3]", + " 0.7 A2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.7]", + " 1 A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]", + " 0 S1 ! Constant in the f curve best-fit for alpha0\u003c=AOA\u003c=alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S2 ! Constant in the f curve best-fit for AOA\u003e alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S3 ! Constant in the f curve best-fit for alpha2\u003c=AOA\u003c alpha0; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S4 ! Constant in the f curve best-fit for AOA\u003c alpha2; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 1.4144 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.", + " -0.5324 Cn2 ! As Cn1 for negative AOAs.", + " 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19]", + " 0.006 Cd0 ! 2D drag coefficient value at 0-lift.", + " -0.121 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0]", + " 0 k0 ! Constant in the \\hat(x)_cp curve best-fit; = (\\hat(x)_AC-0.25). [ignored if UAMod\u003c\u003e1]", + " 0 k1 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k2 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k3 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod\u003c\u003e1]", + " 0.2 x_cp_bar ! Constant in the expression of \\hat(x)_cp^v. [ignored if UAMod\u003c\u003e1, default = 0.2]", + "\"DEFAULT\" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string \"Default\" sets UACutout to 45 degrees]", + "\"DEFAULT\" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5]", + "!........................................", + "! Table of aerodynamics coefficients", + " 142 NumAlf ! Number of data lines in the following table", + "! Alpha Cl Cd Cm", + "! (deg) (-) (-) (-)", + " -180.00 0.000 0.0185 0.0000", + " -175.00 0.394 0.0332 0.1978", + " -170.00 0.788 0.0945 0.3963", + " -160.00 0.670 0.2809 0.2738", + " -155.00 0.749 0.3932 0.3118", + " -150.00 0.797 0.5112 0.3413", + " -145.00 0.818 0.6309 0.3636", + " -140.00 0.813 0.7485 0.3799", + " -135.00 0.786 0.8612 0.3911", + " -130.00 0.739 0.9665 0.3980", + " -125.00 0.675 1.0625 0.4012", + " -120.00 0.596 1.1476 0.4014", + " -115.00 0.505 1.2206 0.3990", + " -110.00 0.403 1.2805 0.3943", + " -105.00 0.294 1.3265 0.3878", + " -100.00 0.179 1.3582 0.3796", + " -95.00 0.060 1.3752 0.3700", + " -90.00 -0.060 1.3774 0.3591", + " -85.00 -0.179 1.3648 0.3471", + " -80.00 -0.295 1.3376 0.3340", + " -75.00 -0.407 1.2962 0.3199", + " -70.00 -0.512 1.2409 0.3049", + " -65.00 -0.608 1.1725 0.2890", + " -60.00 -0.693 1.0919 0.2722", + " -55.00 -0.764 1.0002 0.2545", + " -50.00 -0.820 0.8990 0.2359", + " -45.00 -0.857 0.7900 0.2163", + " -40.00 -0.875 0.6754 0.1958", + " -35.00 -0.869 0.5579 0.1744", + " -30.00 -0.838 0.4405 0.1520", + " -25.00 -0.791 0.3256 0.1262", + " -24.00 -0.794 0.3013 0.1170", + " -23.00 -0.805 0.2762 0.1059", + " -22.00 -0.821 0.2506 0.0931", + " -21.00 -0.843 0.2246 0.0788", + " -20.00 -0.869 0.1983 0.0631", + " -19.00 -0.899 0.1720 0.0464", + " -18.00 -0.931 0.1457 0.0286", + " -17.00 -0.964 0.1197 0.0102", + " -16.00 -0.999 0.0940 -0.0088", + " -15.00 -1.033 0.0689 -0.0281", + " -14.50 -1.050 0.0567 -0.0378", + " -12.01 -0.953 0.0271 -0.0349", + " -11.00 -0.900 0.0303 -0.0361", + " -9.98 -0.827 0.0287 -0.0464", + " -8.12 -0.536 0.0124 -0.0821", + " -7.62 -0.467 0.0109 -0.0924", + " -7.11 -0.393 0.0092 -0.1015", + " -6.60 -0.323 0.0083 -0.1073", + " -6.50 -0.311 0.0089 -0.1083", + " -6.00 -0.245 0.0082 -0.1112", + " -5.50 -0.178 0.0074 -0.1146", + " -5.00 -0.113 0.0069 -0.1172", + " -4.50 -0.048 0.0065 -0.1194", + " -4.00 0.016 0.0063 -0.1213", + " -3.50 0.080 0.0061 -0.1232", + " -3.00 0.145 0.0058 -0.1252", + " -2.50 0.208 0.0057 -0.1268", + " -2.00 0.270 0.0057 -0.1282", + " -1.50 0.333 0.0057 -0.1297", + " -1.00 0.396 0.0057 -0.1310", + " -0.50 0.458 0.0057 -0.1324", + " 0.00 0.521 0.0057 -0.1337", + " 0.50 0.583 0.0057 -0.1350", + " 1.00 0.645 0.0058 -0.1363", + " 1.50 0.706 0.0058 -0.1374", + " 2.00 0.768 0.0059 -0.1385", + " 2.50 0.828 0.0061 -0.1395", + " 3.00 0.888 0.0063 -0.1403", + " 3.50 0.948 0.0066 -0.1406", + " 4.00 0.996 0.0071 -0.1398", + " 4.50 1.046 0.0079 -0.1390", + " 5.00 1.095 0.0090 -0.1378", + " 5.50 1.145 0.0103 -0.1369", + " 6.00 1.192 0.0113 -0.1353", + " 6.50 1.239 0.0122 -0.1338", + " 7.00 1.283 0.0131 -0.1317", + " 7.50 1.324 0.0139 -0.1291", + " 8.00 1.358 0.0147 -0.1249", + " 8.50 1.385 0.0158 -0.1213", + " 9.00 1.403 0.0181 -0.1177", + " 9.50 1.401 0.0211 -0.1142", + " 10.00 1.358 0.0255 -0.1103", + " 10.50 1.313 0.0301 -0.1066", + " 11.00 1.287 0.0347 -0.1032", + " 11.50 1.274 0.0401 -0.1002", + " 12.00 1.272 0.0468 -0.0971", + " 12.50 1.273 0.0545 -0.0940", + " 13.00 1.273 0.0633 -0.0909", + " 13.50 1.273 0.0722 -0.0883", + " 14.00 1.272 0.0806 -0.0865", + " 14.50 1.273 0.0900 -0.0854", + " 15.00 1.275 0.0987 -0.0849", + " 15.50 1.281 0.1075 -0.0847", + " 16.00 1.284 0.1170 -0.0850", + " 16.50 1.296 0.1270 -0.0858", + " 17.00 1.306 0.1368 -0.0869", + " 17.50 1.308 0.1464 -0.0883", + " 18.00 1.308 0.1562 -0.0901", + " 18.50 1.308 0.1664 -0.0922", + " 19.00 1.308 0.1770 -0.0949", + " 19.50 1.307 0.1878 -0.0980", + " 20.00 1.311 0.1987 -0.1017", + " 20.50 1.325 0.2100 -0.1059", + " 21.00 1.324 0.2214 -0.1105", + " 22.00 1.277 0.2499 -0.1172", + " 23.00 1.229 0.2786 -0.1239", + " 24.00 1.182 0.3077 -0.1305", + " 25.00 1.136 0.3371 -0.1370", + " 26.00 1.093 0.3664 -0.1433", + " 28.00 1.017 0.4246 -0.1556", + " 30.00 0.962 0.4813 -0.1671", + " 32.00 0.937 0.5356 -0.1778", + " 35.00 0.947 0.6127 -0.1923", + " 40.00 0.950 0.7396 -0.2154", + " 45.00 0.928 0.8623 -0.2374", + " 50.00 0.884 0.9781 -0.2583", + " 55.00 0.821 1.0846 -0.2782", + " 60.00 0.740 1.1796 -0.2971", + " 65.00 0.646 1.2617 -0.3149", + " 70.00 0.540 1.3297 -0.3318", + " 75.00 0.425 1.3827 -0.3476", + " 80.00 0.304 1.4202 -0.3625", + " 85.00 0.179 1.4423 -0.3763", + " 90.00 0.053 1.4512 -0.3890", + " 95.00 -0.073 1.4480 -0.4004", + " 100.00 -0.198 1.4294 -0.4105", + " 105.00 -0.319 1.3954 -0.4191", + " 110.00 -0.434 1.3464 -0.4260", + " 115.00 -0.541 1.2829 -0.4308", + " 120.00 -0.637 1.2057 -0.4333", + " 125.00 -0.720 1.1157 -0.4330", + " 130.00 -0.787 1.0144 -0.4294", + " 135.00 -0.836 0.9033 -0.4219", + " 140.00 -0.864 0.7845 -0.4098", + " 145.00 -0.869 0.6605 -0.3922", + " 150.00 -0.847 0.5346 -0.3682", + " 155.00 -0.795 0.4103 -0.3364", + " 160.00 -0.711 0.2922 -0.2954", + " 170.00 -0.788 0.0969 -0.3966", + " 175.00 -0.394 0.0334 -0.1978", + " 180.00 0.000 0.0185 0.0000" + ], + "BL_File": { + "Name": "BL_File", + "Type": "Path", + "Desc": "The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + "Line": 415, + "Value": "FileNotFound", + "FileType": "", + "Root": false + } + }, + { + "Name": "NACA64_A17.dat", + "Type": "AirfoilInfo", + "Lines": [ + "! ------------ AirfoilInfo v1.01.x Input File ----------------------------------", + "! NACA64 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN).", + "! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls.", + "! note that this file uses Marshall Buhl's new input file processing; start all comment lines with !", + "! ------------------------------------------------------------------------------", + "\"DEFAULT\" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; \"default\"} [default=1]", + " 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded)", + " 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included.", + "! ......... x-y coordinates are next if NumCoords \u003e 0 .............", + "! x-y coordinate of airfoil reference", + "! x/c y/c", + "0.25 0", + "! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2\u0026t=440", + "! NACA 64-618 (interpolated to 399 points)", + "! x/c y/c", + "1.000000\t0.000000", + "0.990000\t0.003385", + "0.980000\t0.006126", + "0.975000\t0.007447", + "0.970000\t0.008767", + "0.965000\t0.010062", + "0.960000\t0.011357", + "0.955000\t0.012639", + "0.950000\t0.013921", + "0.945000\t0.015200", + "0.940000\t0.016478", + "0.935000\t0.017757", + "0.930000\t0.019036", + "0.925000\t0.020317", + "0.920000\t0.021598", + "0.915000\t0.022881", + "0.910000\t0.024163", + "0.905000\t0.025448", + "0.900000\t0.026733", + "0.887500\t0.029951", + "0.875000\t0.033169", + "0.862500\t0.036386", + "0.850000\t0.039603", + "0.837500\t0.042804", + "0.825000\t0.046004", + "0.812500\t0.049171", + "0.800000\t0.052337", + "0.787500\t0.055452", + "0.775000\t0.058566", + "0.762500\t0.061611", + "0.750000\t0.064656", + "0.737500\t0.067615", + "0.725000\t0.070573", + "0.712500\t0.073429", + "0.700000\t0.076285", + "0.687500\t0.079029", + "0.675000\t0.081773", + "0.662500\t0.084393", + "0.650000\t0.087012", + "0.637500\t0.089490", + "0.625000\t0.091967", + "0.612500\t0.094283", + "0.600000\t0.096599", + "0.587500\t0.098743", + "0.575000\t0.100887", + "0.562500\t0.102843", + "0.550000\t0.104799", + "0.537500\t0.106549", + "0.525000\t0.108299", + "0.512500\t0.109830", + "0.500000\t0.111360", + "0.487500\t0.112649", + "0.475000\t0.113937", + "0.462500\t0.114964", + "0.450000\t0.115990", + "0.445000\t0.116320", + "0.440000\t0.116650", + "0.435000\t0.116931", + "0.430000\t0.117211", + "0.425000\t0.117439", + "0.420000\t0.117667", + "0.415000\t0.117835", + "0.410000\t0.118003", + "0.405000\t0.118104", + "0.400000\t0.118204", + "0.395000\t0.118231", + "0.390000\t0.118258", + "0.385000\t0.118213", + "0.380000\t0.118168", + "0.375000\t0.118057", + "0.370000\t0.117946", + "0.365000\t0.117777", + "0.360000\t0.117607", + "0.355000\t0.117383", + "0.350000\t0.117159", + "0.345000\t0.116881", + "0.340000\t0.116603", + "0.335000\t0.116273", + "0.330000\t0.115942", + "0.325000\t0.115562", + "0.320000\t0.115181", + "0.315000\t0.114750", + "0.310000\t0.114319", + "0.305000\t0.113838", + "0.300000\t0.113356", + "0.295000\t0.112824", + "0.290000\t0.112292", + "0.285000\t0.111710", + "0.280000\t0.111127", + "0.275000\t0.110495", + "0.270000\t0.109863", + "0.265000\t0.109180", + "0.260000\t0.108497", + "0.255000\t0.107762", + "0.250000\t0.107027", + "0.245000\t0.106241", + "0.240000\t0.105454", + "0.235000\t0.104614", + "0.230000\t0.103774", + "0.225000\t0.102880", + "0.220000\t0.101985", + "0.215000\t0.101035", + "0.210000\t0.100084", + "0.205000\t0.099076", + "0.200000\t0.098068", + "0.195000\t0.097001", + "0.190000\t0.095934", + "0.185000\t0.094805", + "0.180000\t0.093676", + "0.175000\t0.092484", + "0.170000\t0.091291", + "0.165000\t0.090032", + "0.160000\t0.088772", + "0.155000\t0.087441", + "0.150000\t0.086110", + "0.145000\t0.084704", + "0.140000\t0.083298", + "0.135000\t0.081814", + "0.130000\t0.080329", + "0.125000\t0.078759", + "0.120000\t0.077188", + "0.115000\t0.075525", + "0.110000\t0.073862", + "0.105000\t0.072098", + "0.100000\t0.070334", + "0.097500\t0.069412", + "0.095000\t0.068489", + "0.092500\t0.067537", + "0.090000\t0.066584", + "0.087500\t0.065601", + "0.085000\t0.064617", + "0.082500\t0.063600", + "0.080000\t0.062583", + "0.077500\t0.061531", + "0.075000\t0.060478", + "0.072500\t0.059388", + "0.070000\t0.058297", + "0.067500\t0.057165", + "0.065000\t0.056032", + "0.062500\t0.054854", + "0.060000\t0.053676", + "0.057500\t0.052447", + "0.055000\t0.051218", + "0.052500\t0.049933", + "0.050000\t0.048647", + "0.047500\t0.047299", + "0.045000\t0.045950", + "0.042500\t0.044530", + "0.040000\t0.043110", + "0.037500\t0.041606", + "0.035000\t0.040102", + "0.032500\t0.038501", + "0.030000\t0.036899", + "0.027500\t0.035177", + "0.025000\t0.033454", + "0.022500\t0.031574", + "0.020000\t0.029694", + "0.018750\t0.028680", + "0.017500\t0.027666", + "0.016250\t0.026589", + "0.015000\t0.025511", + "0.013750\t0.024354", + "0.012500\t0.023197", + "0.011250\t0.021936", + "0.010000\t0.020674", + "0.009500\t0.020131", + "0.009000\t0.019587", + "0.008500\t0.019017", + "0.008000\t0.018447", + "0.007500\t0.017844", + "0.007000\t0.017241", + "0.006500\t0.016598", + "0.006000\t0.015955", + "0.005500\t0.015260", + "0.005000\t0.014565", + "0.004500\t0.013801", + "0.004000\t0.013037", + "0.003500\t0.012167", + "0.003000\t0.011296", + "0.002500\t0.010262", + "0.002000\t0.009227", + "0.001875\t0.008930", + "0.001750\t0.008633", + "0.001625\t0.008315", + "0.001500\t0.007997", + "0.001375\t0.007655", + "0.001250\t0.007312", + "0.001125\t0.006934", + "0.001000\t0.006555", + "0.000875\t0.006125", + "0.000750\t0.005695", + "0.000625\t0.005184", + "0.000500\t0.004672", + "0.000400\t0.004190", + "0.000350\t0.003913", + "0.000300\t0.003636", + "0.000200\t0.002970", + "0.000100\t0.002104", + "0.000050\t0.001052", + "0.000000\t0.000000", + "0.000050\t-0.001046", + "0.000100\t-0.002092", + "0.000200\t-0.002954", + "0.000300\t-0.003613", + "0.000350\t-0.003891", + "0.000400\t-0.004169", + "0.000500\t-0.004658", + "0.000625\t-0.005178", + "0.000750\t-0.005698", + "0.000875\t-0.006135", + "0.001000\t-0.006572", + "0.001125\t-0.006956", + "0.001250\t-0.007340", + "0.001375\t-0.007684", + "0.001500\t-0.008027", + "0.001625\t-0.008341", + "0.001750\t-0.008654", + "0.001875\t-0.008943", + "0.002000\t-0.009231", + "0.002500\t-0.010204", + "0.003000\t-0.011176", + "0.003500\t-0.011953", + "0.004000\t-0.012729", + "0.004500\t-0.013380", + "0.005000\t-0.014030", + "0.005500\t-0.014595", + "0.006000\t-0.015160", + "0.006500\t-0.015667", + "0.007000\t-0.016174", + "0.007500\t-0.016636", + "0.008000\t-0.017098", + "0.008500\t-0.017526", + "0.009000\t-0.017953", + "0.009500\t-0.018352", + "0.010000\t-0.018750", + "0.011250\t-0.019644", + "0.012500\t-0.020537", + "0.013750\t-0.021322", + "0.015000\t-0.022107", + "0.016250\t-0.022812", + "0.017500\t-0.023517", + "0.018750\t-0.024160", + "0.020000\t-0.024803", + "0.022500\t-0.025948", + "0.025000\t-0.027092", + "0.027500\t-0.028097", + "0.030000\t-0.029102", + "0.032500\t-0.030003", + "0.035000\t-0.030904", + "0.037500\t-0.031725", + "0.040000\t-0.032546", + "0.042500\t-0.033304", + "0.045000\t-0.034061", + "0.047500\t-0.034767", + "0.050000\t-0.035472", + "0.052500\t-0.036132", + "0.055000\t-0.036792", + "0.057500\t-0.037414", + "0.060000\t-0.038035", + "0.062500\t-0.038622", + "0.065000\t-0.039209", + "0.067500\t-0.039766", + "0.070000\t-0.040322", + "0.072500\t-0.040852", + "0.075000\t-0.041381", + "0.077500\t-0.041885", + "0.080000\t-0.042389", + "0.082500\t-0.042870", + "0.085000\t-0.043350", + "0.087500\t-0.043809", + "0.090000\t-0.044268", + "0.092500\t-0.044707", + "0.095000\t-0.045145", + "0.097500\t-0.045566", + "0.100000\t-0.045987", + "0.105000\t-0.046782", + "0.110000\t-0.047576", + "0.115000\t-0.048313", + "0.120000\t-0.049050", + "0.125000\t-0.049734", + "0.130000\t-0.050417", + "0.135000\t-0.051053", + "0.140000\t-0.051688", + "0.145000\t-0.052278", + "0.150000\t-0.052868", + "0.155000\t-0.053418", + "0.160000\t-0.053967", + "0.165000\t-0.054478", + "0.170000\t-0.054988", + "0.175000\t-0.055461", + "0.180000\t-0.055934", + "0.185000\t-0.056373", + "0.190000\t-0.056811", + "0.195000\t-0.057216", + "0.200000\t-0.057621", + "0.205000\t-0.057993", + "0.210000\t-0.058365", + "0.215000\t-0.058705", + "0.220000\t-0.059045", + "0.225000\t-0.059355", + "0.230000\t-0.059664", + "0.235000\t-0.059944", + "0.240000\t-0.060224", + "0.245000\t-0.060474", + "0.250000\t-0.060723", + "0.255000\t-0.060943", + "0.260000\t-0.061163", + "0.265000\t-0.061354", + "0.270000\t-0.061545", + "0.275000\t-0.061708", + "0.280000\t-0.061871", + "0.285000\t-0.062004", + "0.290000\t-0.062137", + "0.295000\t-0.062240", + "0.300000\t-0.062343", + "0.305000\t-0.062417", + "0.310000\t-0.062490", + "0.315000\t-0.062534", + "0.320000\t-0.062577", + "0.325000\t-0.062590", + "0.330000\t-0.062602", + "0.335000\t-0.062583", + "0.340000\t-0.062563", + "0.345000\t-0.062512", + "0.350000\t-0.062460", + "0.355000\t-0.062374", + "0.360000\t-0.062287", + "0.365000\t-0.062164", + "0.370000\t-0.062040", + "0.375000\t-0.061878", + "0.380000\t-0.061716", + "0.385000\t-0.061509", + "0.390000\t-0.061301", + "0.395000\t-0.061040", + "0.400000\t-0.060778", + "0.405000\t-0.060458", + "0.410000\t-0.060138", + "0.415000\t-0.059763", + "0.420000\t-0.059388", + "0.425000\t-0.058966", + "0.430000\t-0.058544", + "0.435000\t-0.058083", + "0.440000\t-0.057622", + "0.445000\t-0.057127", + "0.450000\t-0.056632", + "0.462500\t-0.055265", + "0.475000\t-0.053897", + "0.487500\t-0.052374", + "0.500000\t-0.050850", + "0.512500\t-0.049195", + "0.525000\t-0.047539", + "0.537500\t-0.045777", + "0.550000\t-0.044014", + "0.562500\t-0.042165", + "0.575000\t-0.040316", + "0.587500\t-0.038401", + "0.600000\t-0.036486", + "0.612500\t-0.034526", + "0.625000\t-0.032565", + "0.637500\t-0.030575", + "0.650000\t-0.028585", + "0.662500\t-0.026594", + "0.675000\t-0.024603", + "0.687500\t-0.022632", + "0.700000\t-0.020660", + "0.712500\t-0.018728", + "0.725000\t-0.016795", + "0.737500\t-0.014922", + "0.750000\t-0.013048", + "0.762500\t-0.011260", + "0.775000\t-0.009472", + "0.787500\t-0.007797", + "0.800000\t-0.006122", + "0.812500\t-0.004594", + "0.825000\t-0.003065", + "0.837500\t-0.001721", + "0.850000\t-0.000376", + "0.862500\t0.000742", + "0.875000\t0.001859", + "0.887500\t0.002698", + "0.900000\t0.003536", + "0.905000\t0.003780", + "0.910000\t0.004023", + "0.915000\t0.004205", + "0.920000\t0.004387", + "0.925000\t0.004504", + "0.930000\t0.004620", + "0.935000\t0.004661", + "0.940000\t0.004702", + "0.945000\t0.004658", + "0.950000\t0.004614", + "0.955000\t0.004476", + "0.960000\t0.004338", + "0.965000\t0.004084", + "0.970000\t0.003829", + "0.975000\t0.003436", + "0.980000\t0.003042", + "0.990000\t0.001910", + "1.000000\t0.000000", + "\"unused\" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + " 1 NumTabs ! Number of airfoil tables in this file.", + "! ------------------------------------------------------------------------------", + "! data for table 1", + "! ------------------------------------------------------------------------------", + " 0.75 Re ! Reynolds number in millions", + " 0 UserProp ! User property (control) setting", + "True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line", + "!........................................", + " -4.432 alpha0 ! 0-lift angle of attack, depends on airfoil.", + " 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003ealpha0. (deg)", + " -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA\u003calpha0. (deg)", + " 1 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)", + " 6.0031 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)", + "\"Default\" T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]", + "\"Default\" T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on Re,M, and airfoil class. [default = 6]", + "\"Default\" T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]", + "\"Default\" T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]", + "\"Default\" b1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.14]", + "\"Default\" b2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.53]", + "\"Default\" b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]", + "\"Default\" A1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.3]", + "\"Default\" A2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.7]", + "\"Default\" A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]", + " 0 S1 ! Constant in the f curve best-fit for alpha0\u003c=AOA\u003c=alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S2 ! Constant in the f curve best-fit for AOA\u003e alpha1; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S3 ! Constant in the f curve best-fit for alpha2\u003c=AOA\u003c alpha0; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 0 S4 ! Constant in the f curve best-fit for AOA\u003c alpha2; by definition it depends on the airfoil. [ignored if UAMod\u003c\u003e1]", + " 1.4073 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.", + " -0.7945 Cn2 ! As Cn1 for negative AOAs.", + " 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19]", + " 0.0065 Cd0 ! 2D drag coefficient value at 0-lift.", + " -0.088 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0]", + " 0 k0 ! Constant in the \\hat(x)_cp curve best-fit; = (\\hat(x)_AC-0.25). [ignored if UAMod\u003c\u003e1]", + " 0 k1 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k2 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k3 ! Constant in the \\hat(x)_cp curve best-fit. [ignored if UAMod\u003c\u003e1]", + " 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod\u003c\u003e1]", + "\"Default\" x_cp_bar ! Constant in the expression of \\hat(x)_cp^v. [ignored if UAMod\u003c\u003e1, default = 0.2]", + "\"Default\" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string \"Default\" sets UACutout to 45 degrees]", + "\"DEFAULT\" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5]", + "!........................................", + "! Table of aerodynamics coefficients", + " 127 NumAlf ! Number of data lines in the following table", + "! Alpha Cl Cd Cm", + "! (deg) (-) (-) (-)", + " -180.00 0.000 0.0198 0.0000", + " -175.00 0.374 0.0341 0.1880", + " -170.00 0.749 0.0955 0.3770", + " -160.00 0.659 0.2807 0.2747", + " -155.00 0.736 0.3919 0.3130", + " -150.00 0.783 0.5086 0.3428", + " -145.00 0.803 0.6267 0.3654", + " -140.00 0.798 0.7427 0.3820", + " -135.00 0.771 0.8537 0.3935", + " -130.00 0.724 0.9574 0.4007", + " -125.00 0.660 1.0519 0.4042", + " -120.00 0.581 1.1355 0.4047", + " -115.00 0.491 1.2070 0.4025", + " -110.00 0.390 1.2656 0.3981", + " -105.00 0.282 1.3104 0.3918", + " -100.00 0.169 1.3410 0.3838", + " -95.00 0.052 1.3572 0.3743", + " -90.00 -0.067 1.3587 0.3636", + " -85.00 -0.184 1.3456 0.3517", + " -80.00 -0.299 1.3181 0.3388", + " -75.00 -0.409 1.2765 0.3248", + " -70.00 -0.512 1.2212 0.3099", + " -65.00 -0.606 1.1532 0.2940", + " -60.00 -0.689 1.0731 0.2772", + " -55.00 -0.759 0.9822 0.2595", + " -50.00 -0.814 0.8820 0.2409", + " -45.00 -0.850 0.7742 0.2212", + " -40.00 -0.866 0.6610 0.2006", + " -35.00 -0.860 0.5451 0.1789", + " -30.00 -0.829 0.4295 0.1563", + " -25.00 -0.853 0.3071 0.1156", + " -24.00 -0.870 0.2814 0.1040", + " -23.00 -0.890 0.2556 0.0916", + " -22.00 -0.911 0.2297 0.0785", + " -21.00 -0.934 0.2040 0.0649", + " -20.00 -0.958 0.1785 0.0508", + " -19.00 -0.982 0.1534 0.0364", + " -18.00 -1.005 0.1288 0.0218", + " -17.00 -1.082 0.1037 0.0129", + " -16.00 -1.113 0.0786 -0.0028", + " -15.00 -1.105 0.0535 -0.0251", + " -14.00 -1.078 0.0283 -0.0419", + " -13.50 -1.053 0.0158 -0.0521", + " -13.00 -1.015 0.0151 -0.0610", + " -12.00 -0.904 0.0134 -0.0707", + " -11.00 -0.807 0.0121 -0.0722", + " -10.00 -0.711 0.0111 -0.0734", + " -9.00 -0.595 0.0099 -0.0772", + " -8.00 -0.478 0.0091 -0.0807", + " -7.00 -0.375 0.0086 -0.0825", + " -6.00 -0.264 0.0082 -0.0832", + " -5.00 -0.151 0.0079 -0.0841", + " -4.00 -0.017 0.0072 -0.0869", + " -3.00 0.088 0.0064 -0.0912", + " -2.00 0.213 0.0054 -0.0946", + " -1.00 0.328 0.0052 -0.0971", + " 0.00 0.442 0.0052 -0.1014", + " 1.00 0.556 0.0052 -0.1076", + " 2.00 0.670 0.0053 -0.1126", + " 3.00 0.784 0.0053 -0.1157", + " 4.00 0.898 0.0054 -0.1199", + " 5.00 1.011 0.0058 -0.1240", + " 6.00 1.103 0.0091 -0.1234", + " 7.00 1.181 0.0113 -0.1184", + " 8.00 1.257 0.0124 -0.1163", + " 8.50 1.293 0.0130 -0.1163", + " 9.00 1.326 0.0136 -0.1160", + " 9.50 1.356 0.0143 -0.1154", + " 10.00 1.382 0.0150 -0.1149", + " 10.50 1.400 0.0267 -0.1145", + " 11.00 1.415 0.0383 -0.1143", + " 11.50 1.425 0.0498 -0.1147", + " 12.00 1.434 0.0613 -0.1158", + " 12.50 1.443 0.0727 -0.1165", + " 13.00 1.451 0.0841 -0.1153", + " 13.50 1.453 0.0954 -0.1131", + " 14.00 1.448 0.1065 -0.1112", + " 14.50 1.444 0.1176 -0.1101", + " 15.00 1.445 0.1287 -0.1103", + " 15.50 1.447 0.1398 -0.1109", + " 16.00 1.448 0.1509 -0.1114", + " 16.50 1.444 0.1619 -0.1111", + " 17.00 1.438 0.1728 -0.1097", + " 17.50 1.439 0.1837 -0.1079", + " 18.00 1.448 0.1947 -0.1080", + " 18.50 1.452 0.2057 -0.1090", + " 19.00 1.448 0.2165 -0.1086", + " 19.50 1.438 0.2272 -0.1077", + " 20.00 1.428 0.2379 -0.1099", + " 21.00 1.401 0.2590 -0.1169", + " 22.00 1.359 0.2799 -0.1190", + " 23.00 1.300 0.3004 -0.1235", + " 24.00 1.220 0.3204 -0.1393", + " 25.00 1.168 0.3377 -0.1440", + " 26.00 1.116 0.3554 -0.1486", + " 28.00 1.015 0.3916 -0.1577", + " 30.00 0.926 0.4294 -0.1668", + " 32.00 0.855 0.4690 -0.1759", + " 35.00 0.800 0.5324 -0.1897", + " 40.00 0.804 0.6452 -0.2126", + " 45.00 0.793 0.7573 -0.2344", + " 50.00 0.763 0.8664 -0.2553", + " 55.00 0.717 0.9708 -0.2751", + " 60.00 0.656 1.0693 -0.2939", + " 65.00 0.582 1.1606 -0.3117", + " 70.00 0.495 1.2438 -0.3285", + " 75.00 0.398 1.3178 -0.3444", + " 80.00 0.291 1.3809 -0.3593", + " 85.00 0.176 1.4304 -0.3731", + " 90.00 0.053 1.4565 -0.3858", + " 95.00 -0.074 1.4533 -0.3973", + " 100.00 -0.199 1.4345 -0.4075", + " 105.00 -0.321 1.4004 -0.4162", + " 110.00 -0.436 1.3512 -0.4231", + " 115.00 -0.543 1.2874 -0.4280", + " 120.00 -0.640 1.2099 -0.4306", + " 125.00 -0.723 1.1196 -0.4304", + " 130.00 -0.790 1.0179 -0.4270", + " 135.00 -0.840 0.9064 -0.4196", + " 140.00 -0.868 0.7871 -0.4077", + " 145.00 -0.872 0.6627 -0.3903", + " 150.00 -0.850 0.5363 -0.3665", + " 155.00 -0.798 0.4116 -0.3349", + " 160.00 -0.714 0.2931 -0.2942", + " 170.00 -0.749 0.0971 -0.3771", + " 175.00 -0.374 0.0334 -0.1879", + " 180.00 0.000 0.0198 0.0000" + ], + "BL_File": { + "Name": "BL_File", + "Type": "Path", + "Desc": "The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called.", + "Line": 415, + "Value": "FileNotFound", + "FileType": "", + "Root": false + } + } + ] + }, + "Notes": [] + }, + "Analysis": { + "Cases": [ + { + "ID": 1, + "Name": "Base", + "IncludeAero": false, + "UseController": false, + "RotorSpeedRange": { + "Min": 3, + "Max": 25, + "Num": 5 + }, + "WindSpeedRange": { + "Min": 1, + "Max": 20, + "Num": 5 + }, + "RatedWindSpeed": 10, + "RatedRotorSpeed": 0, + "TrimGain": [ + 100, + 0.00001 + ], + "Curve": [ + { + "ID": 1, + "WindSpeed": 1, + "RotorSpeed": 3, + "BladePitch": 0 + }, + { + "ID": 2, + "WindSpeed": 20, + "RotorSpeed": 25, + "BladePitch": 0 + } + ], + "OperatingPoints": [ + { + "ID": 0, + "WindSpeed": 0, + "RotorSpeed": 3, + "BladePitch": 0 + }, + { + "ID": 1, + "WindSpeed": 0, + "RotorSpeed": 8.5, + "BladePitch": 0 + }, + { + "ID": 2, + "WindSpeed": 0, + "RotorSpeed": 14, + "BladePitch": 0 + }, + { + "ID": 3, + "WindSpeed": 0, + "RotorSpeed": 19.5, + "BladePitch": 0 + }, + { + "ID": 4, + "WindSpeed": 0, + "RotorSpeed": 25, + "BladePitch": 0 + } + ] + } + ] + }, + "Evaluate": { + "ExecPath": "/Users/dslaught/projects/openfast-mac/install/bin/openfast", + "ExecVersion": "OpenFAST-v3.5.3-dirty\n Compile Info:\n - Compiler: GCC version 13.2.0\n - Architecture: 64 bit\n - Precision: double\n - OpenMP: No\n - Date: Apr 17 2024\n - Time: 12:48:37", + "ExecValid": true, + "MaxCPUs": 10, + "NumCPUs": 1, + "FilesOnly": false + }, + "Results": null, + "Diagram": null +} \ No newline at end of file diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_AeroDyn15.dat b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_AeroDyn15.dat new file mode 100644 index 0000000..e31c794 --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_AeroDyn15.dat @@ -0,0 +1,95 @@ +------- AERODYN v15 for OpenFAST INPUT FILE ----------------------------------------------- +NREL 5.0 MW offshore baseline aerodynamic input properties, with OC3 Monopile tower +====== General Options ============================================================================ +False Echo - Echo the input to ".AD.ech"? (flag) +"default" DTAero - Time interval for aerodynamic calculations {or "default"} (s) + 1 WakeMod - Type of wake/induction model (switch) {0=none, 1=BEMT, 2=DBEMT, 3=OLAF} [WakeMod cannot be 2 or 3 when linearizing] + 2 AFAeroMod - Type of blade airfoil aerodynamics model (switch) {1=steady model, 2=Beddoes-Leishman unsteady model} [AFAeroMod must be 1 when linearizing] + 1 TwrPotent - Type tower influence on wind based on potential flow around the tower (switch) {0=none, 1=baseline potential flow, 2=potential flow with Bak correction} + 0 TwrShadow - Calculate tower influence on wind based on downstream tower shadow (switch) {0=none, 1=Powles model, 2=Eames model} +True TwrAero - Calculate tower aerodynamic loads? (flag) +False FrozenWake - Assume frozen wake during linearization? (flag) [used only when WakeMod=1 and when linearizing] +False CavitCheck - Perform cavitation check? (flag) [AFAeroMod must be 1 when CavitCheck=true] +False Buoyancy - Include buoyancy effects? (flag) +False CompAA - Flag to compute AeroAcoustics calculation [used only when WakeMod = 1 or 2] +"unused" AA_InputFile - AeroAcoustics input file [used only when CompAA=true] +====== Environmental Conditions =================================================================== +"default" AirDens - Air density (kg/m^3) +"default" KinVisc - Kinematic viscosity of working fluid (m^2/s) +"default" SpdSound - Speed of sound in working fluid (m/s) +"default" Patm - Atmospheric pressure (Pa) [used only when CavitCheck=True] +"default" Pvap - Vapour pressure of working fluid (Pa) [used only when CavitCheck=True] +====== Blade-Element/Momentum Theory Options ====================================================== [unused when WakeMod=0 or 3] + 2 SkewMod - Type of skewed-wake correction model (switch) {1=uncoupled, 2=Pitt/Peters, 3=coupled} [unused when WakeMod=0 or 3] +"default" SkewModFactor - Constant used in Pitt/Peters skewed wake model {or "default" is 15/32*pi} (-) [used only when SkewMod=2; unused when WakeMod=0 or 3] +True TipLoss - Use the Prandtl tip-loss model? (flag) [unused when WakeMod=0 or 3] +True HubLoss - Use the Prandtl hub-loss model? (flag) [unused when WakeMod=0 or 3] +True TanInd - Include tangential induction in BEMT calculations? (flag) [unused when WakeMod=0 or 3] +False AIDrag - Include the drag term in the axial-induction calculation? (flag) [unused when WakeMod=0 or 3] +False TIDrag - Include the drag term in the tangential-induction calculation? (flag) [unused when WakeMod=0,3 or TanInd=FALSE] +"Default" IndToler - Convergence tolerance for BEMT nonlinear solve residual equation {or "default"} (-) [unused when WakeMod=0 or 3] + 100 MaxIter - Maximum number of iteration steps (-) [unused when WakeMod=0] +====== Dynamic Blade-Element/Momentum Theory Options ============================================== [used only when WakeMod=2] + 2 DBEMT_Mod - Type of dynamic BEMT (DBEMT) model {1=constant tau1, 2=time-dependent tau1, 3=constant tau1 with continuous formulation} (-) [used only when WakeMod=2] + 4 tau1_const - Time constant for DBEMT (s) [used only when WakeMod=2 and DBEMT_Mod=1 or 3] +====== OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options ================== [used only when WakeMod=3] +"unused" OLAFInputFileName - Input file for OLAF [used only when WakeMod=3] +====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2] + 3 UAMod - Unsteady Aero Model Switch (switch) {2=B-L Gonzalez, 3=B-L Minnema/Pierce, 4=B-L HGM 4-states, 5=B-L 5 states, 6=Oye, 7=Boeing-Vertol} [used only when AFAeroMod=2] +True FLookup - Flag to indicate whether a lookup for f' will be calculated (TRUE) or whether best-fit exponential equations will be used (FALSE); if FALSE S1-S4 must be provided in airfoil input files (flag) [used only when AFAeroMod=2] +====== Airfoil Information ========================================================================= + 1 AFTabMod - Interpolation method for multiple airfoil tables {1=1D interpolation on AoA (first table only); 2=2D interpolation on AoA and Re; 3=2D interpolation on AoA and UserProp} (-) + 1 InCol_Alfa - The column in the airfoil tables that contains the angle of attack (-) + 2 InCol_Cl - The column in the airfoil tables that contains the lift coefficient (-) + 3 InCol_Cd - The column in the airfoil tables that contains the drag coefficient (-) + 4 InCol_Cm - The column in the airfoil tables that contains the pitching-moment coefficient; use zero if there is no Cm column (-) + 0 InCol_Cpmin - The column in the airfoil tables that contains the Cpmin coefficient; use zero if there is no Cpmin column (-) + 8 NumAFfiles - Number of airfoil files used (-) +"Airfoils/Cylinder1.dat" AFNames - Airfoil file names (NumAFfiles lines) (quoted strings) +"Airfoils/Cylinder2.dat" +"Airfoils/DU40_A17.dat" +"Airfoils/DU35_A17.dat" +"Airfoils/DU30_A17.dat" +"Airfoils/DU25_A17.dat" +"Airfoils/DU21_A17.dat" +"Airfoils/NACA64_A17.dat" +====== Rotor/Blade Properties ===================================================================== +True UseBlCm - Include aerodynamic pitching moment in calculations? (flag) +"NREL_5MW_AeroDyn_blade.dat" ADBlFile(1) - Name of file containing distributed aerodynamic properties for Blade #1 (-) +"NREL_5MW_AeroDyn_blade.dat" ADBlFile(2) - Name of file containing distributed aerodynamic properties for Blade #2 (-) [unused if NumBl < 2] +"NREL_5MW_AeroDyn_blade.dat" ADBlFile(3) - Name of file containing distributed aerodynamic properties for Blade #3 (-) [unused if NumBl < 3] +====== Hub Properties ============================================================================== [used only when Buoyancy=True] +0.0 VolHub - Hub volume (m^3) +0.0 HubCenBx - Hub center of buoyancy x direction offset (m) +====== Nacelle Properties ========================================================================== [used only when Buoyancy=True] +0.0 VolNac - Nacelle volume (m^3) +0,0,0 NacCenB - Position of nacelle center of buoyancy from yaw bearing in nacelle coordinates (m) +====== Tail fin Aerodynamics ======================================================================== +False TFinAero - Calculate tail fin aerodynamics model (flag) +"unused" TFinFile - Input file for tail fin aerodynamics [used only when TFinAero=True] +====== Tower Influence and Aerodynamics ============================================================ [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] + 11 NumTwrNds - Number of tower nodes used in the analysis (-) [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] +TwrElev TwrDiam TwrCd TwrTI TwrCb !TwrTI used only with TwrShadow=2, TwrCb used only with Buoyancy=True +(m) (m) (-) (-) (-) +1.0000000E+01 6.0000000E+00 1.0000000E+00 1.0000000E-01 0.0 +1.7760000E+01 5.7870000E+00 1.0000000E+00 1.0000000E-01 0.0 +2.5520000E+01 5.5740000E+00 1.0000000E+00 1.0000000E-01 0.0 +3.3280000E+01 5.3610000E+00 1.0000000E+00 1.0000000E-01 0.0 +4.1040000E+01 5.1480000E+00 1.0000000E+00 1.0000000E-01 0.0 +4.8800000E+01 4.9350000E+00 1.0000000E+00 1.0000000E-01 0.0 +5.6560000E+01 4.7220000E+00 1.0000000E+00 1.0000000E-01 0.0 +6.4320000E+01 4.5090000E+00 1.0000000E+00 1.0000000E-01 0.0 +7.2080000E+01 4.2960000E+00 1.0000000E+00 1.0000000E-01 0.0 +7.9840000E+01 4.0830000E+00 1.0000000E+00 1.0000000E-01 0.0 +8.7600000E+01 3.8700000E+00 1.0000000E+00 1.0000000E-01 0.0 +====== Outputs ==================================================================================== +True SumPrint - Generate a summary file listing input options and interpolated properties to ".AD.sum"? (flag) + 0 NBlOuts - Number of blade node outputs [0 - 9] (-) + 2, 9, 16, 4, 5, 7, 11, 13, 14 BlOutNd - Blade nodes whose values will be output (-) + 0 NTwOuts - Number of tower node outputs [0 - 9] (-) + 1, 2, 3, 4, 5 TwOutNd - Tower nodes whose values will be output (-) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +"RtAeroFxh, RtAeroFyh, RtAeroFzh" +"RtAeroMxh, RtAeroMyh, RtAeroMzh" +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +--------------------------------------------------------------------------------------- diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ElastoDyn.dat b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ElastoDyn.dat new file mode 100644 index 0000000..a226c38 --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ElastoDyn.dat @@ -0,0 +1,135 @@ +------- ELASTODYN for OpenFAST INPUT FILE ------------------------------------------- +NREL 5.0 MW Baseline Wind Turbine for Use in Offshore Analysis. Properties from Dutch Offshore Wind Energy Converter (DOWEC) 6MW Pre-Design (10046_009.pdf) and REpower 5M 5MW (5m_uk.pdf); +---------------------- SIMULATION CONTROL -------------------------------------- +False Echo - Echo input data to ".ech" (flag) + 3 Method - Integration method: {1: RK4, 2: AB4, or 3: ABM4} (-) +"default" DT - Integration time step (s) +---------------------- DEGREES OF FREEDOM -------------------------------------- +True FlapDOF1 - First flapwise blade mode DOF (flag) +True FlapDOF2 - Second flapwise blade mode DOF (flag) +True EdgeDOF - First edgewise blade mode DOF (flag) +False TeetDOF - Rotor-teeter DOF (flag) [unused for 3 blades] +True DrTrDOF - Drivetrain rotational-flexibility DOF (flag) +True GenDOF - Generator DOF (flag) +True YawDOF - Yaw DOF (flag) +True TwFADOF1 - First fore-aft tower bending-mode DOF (flag) +True TwFADOF2 - Second fore-aft tower bending-mode DOF (flag) +True TwSSDOF1 - First side-to-side tower bending-mode DOF (flag) +True TwSSDOF2 - Second side-to-side tower bending-mode DOF (flag) +True PtfmSgDOF - Platform horizontal surge translation DOF (flag) +True PtfmSwDOF - Platform horizontal sway translation DOF (flag) +True PtfmHvDOF - Platform vertical heave translation DOF (flag) +True PtfmRDOF - Platform roll tilt rotation DOF (flag) +True PtfmPDOF - Platform pitch tilt rotation DOF (flag) +True PtfmYDOF - Platform yaw rotation DOF (flag) +---------------------- INITIAL CONDITIONS -------------------------------------- + 0 OoPDefl - Initial out-of-plane blade-tip displacement (meters) + 0 IPDefl - Initial in-plane blade-tip deflection (meters) + 0 BlPitch(1) - Blade 1 initial pitch (degrees) + 0 BlPitch(2) - Blade 2 initial pitch (degrees) + 0 BlPitch(3) - Blade 3 initial pitch (degrees) [unused for 2 blades] + 0 TeetDefl - Initial or fixed teeter angle (degrees) [unused for 3 blades] + 0 Azimuth - Initial azimuth angle for blade 1 (degrees) + 12.1 RotSpeed - Initial or fixed rotor speed (rpm) + 0 NacYaw - Initial or fixed nacelle-yaw angle (degrees) + 0 TTDspFA - Initial fore-aft tower-top displacement (meters) + 0 TTDspSS - Initial side-to-side tower-top displacement (meters) + 0 PtfmSurge - Initial or fixed horizontal surge translational displacement of platform (meters) + 0 PtfmSway - Initial or fixed horizontal sway translational displacement of platform (meters) + -0.0009 PtfmHeave - Initial or fixed vertical heave translational displacement of platform (meters) + 0 PtfmRoll - Initial or fixed roll tilt rotational displacement of platform (degrees) + 0 PtfmPitch - Initial or fixed pitch tilt rotational displacement of platform (degrees) + 0 PtfmYaw - Initial or fixed yaw rotational displacement of platform (degrees) +---------------------- TURBINE CONFIGURATION ----------------------------------- + 3 NumBl - Number of blades (-) + 63 TipRad - The distance from the rotor apex to the blade tip (meters) + 1.5 HubRad - The distance from the rotor apex to the blade root (meters) + -2.5 PreCone(1) - Blade 1 cone angle (degrees) + -2.5 PreCone(2) - Blade 2 cone angle (degrees) + -2.5 PreCone(3) - Blade 3 cone angle (degrees) [unused for 2 blades] + 0 HubCM - Distance from rotor apex to hub mass [positive downwind] (meters) + 0 UndSling - Undersling length [distance from teeter pin to the rotor apex] (meters) [unused for 3 blades] + 0 Delta3 - Delta-3 angle for teetering rotors (degrees) [unused for 3 blades] + 0 AzimB1Up - Azimuth value to use for I/O when blade 1 points up (degrees) + -5.0191 OverHang - Distance from yaw axis to rotor apex [3 blades] or teeter pin [2 blades] (meters) + 1.912 ShftGagL - Distance from rotor apex [3 blades] or teeter pin [2 blades] to shaft strain gages [positive for upwind rotors] (meters) + -5 ShftTilt - Rotor shaft tilt angle (degrees) + 1.9 NacCMxn - Downwind distance from the tower-top to the nacelle CM (meters) + 0 NacCMyn - Lateral distance from the tower-top to the nacelle CM (meters) + 1.75 NacCMzn - Vertical distance from the tower-top to the nacelle CM (meters) + -3.09528 NcIMUxn - Downwind distance from the tower-top to the nacelle IMU (meters) + 0 NcIMUyn - Lateral distance from the tower-top to the nacelle IMU (meters) + 2.23336 NcIMUzn - Vertical distance from the tower-top to the nacelle IMU (meters) + 1.96256 Twr2Shft - Vertical distance from the tower-top to the rotor shaft (meters) + 87.6 TowerHt - Height of tower relative to ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] (meters) + 10 TowerBsHt - Height of tower base relative to ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] (meters) + 0 PtfmCMxt - Downwind distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform CM (meters) + 0 PtfmCMyt - Lateral distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform CM (meters) + 10 PtfmCMzt - Vertical distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform CM (meters) + 10 PtfmRefzt - Vertical distance from the ground level [onshore], MSL [offshore wind or floating MHK], or seabed [fixed MHK] to the platform reference point (meters) +---------------------- MASS AND INERTIA ---------------------------------------- + 0 TipMass(1) - Tip-brake mass, blade 1 (kg) + 0 TipMass(2) - Tip-brake mass, blade 2 (kg) + 0 TipMass(3) - Tip-brake mass, blade 3 (kg) [unused for 2 blades] + 56780 HubMass - Hub mass (kg) + 115926 HubIner - Hub inertia about rotor axis [3 blades] or teeter axis [2 blades] (kg m^2) + 534.116 GenIner - Generator inertia about HSS (kg m^2) + 240000 NacMass - Nacelle mass (kg) +2.60789E+06 NacYIner - Nacelle inertia about yaw axis (kg m^2) + 0 YawBrMass - Yaw bearing mass (kg) + 0 PtfmMass - Platform mass (kg) + 0 PtfmRIner - Platform inertia for roll tilt rotation about the platform CM (kg m^2) + 0 PtfmPIner - Platform inertia for pitch tilt rotation about the platform CM (kg m^2) + 1.534E+06 PtfmYIner - Platform inertia for yaw rotation about the platform CM (kg m^2) +---------------------- BLADE --------------------------------------------------- + 17 BldNodes - Number of blade nodes (per blade) used for analysis (-) +"NREL_5MW_ElastoDyn_Blade.dat" BldFile(1) - Name of file containing properties for blade 1 (quoted string) +"NREL_5MW_ElastoDyn_Blade.dat" BldFile(2) - Name of file containing properties for blade 2 (quoted string) +"NREL_5MW_ElastoDyn_Blade.dat" BldFile(3) - Name of file containing properties for blade 3 (quoted string) [unused for 2 blades] +---------------------- ROTOR-TEETER -------------------------------------------- + 0 TeetMod - Rotor-teeter spring/damper model {0: none, 1: standard, 2: user-defined from routine UserTeet} (switch) [unused for 3 blades] + 0 TeetDmpP - Rotor-teeter damper position (degrees) [used only for 2 blades and when TeetMod=1] + 0 TeetDmp - Rotor-teeter damping constant (N-m/(rad/s)) [used only for 2 blades and when TeetMod=1] + 0 TeetCDmp - Rotor-teeter rate-independent Coulomb-damping moment (N-m) [used only for 2 blades and when TeetMod=1] + 0 TeetSStP - Rotor-teeter soft-stop position (degrees) [used only for 2 blades and when TeetMod=1] + 0 TeetHStP - Rotor-teeter hard-stop position (degrees) [used only for 2 blades and when TeetMod=1] + 0 TeetSSSp - Rotor-teeter soft-stop linear-spring constant (N-m/rad) [used only for 2 blades and when TeetMod=1] + 0 TeetHSSp - Rotor-teeter hard-stop linear-spring constant (N-m/rad) [used only for 2 blades and when TeetMod=1] +---------------------- DRIVETRAIN ---------------------------------------------- + 100 GBoxEff - Gearbox efficiency (%) + 97 GBRatio - Gearbox ratio (-) +8.67637E+08 DTTorSpr - Drivetrain torsional spring (N-m/rad) + 6.215E+06 DTTorDmp - Drivetrain torsional damper (N-m/(rad/s)) +---------------------- FURLING ------------------------------------------------- +False Furling - Read in additional model properties for furling turbine (flag) [must currently be FALSE) +"unused" FurlFile - Name of file containing furling properties (quoted string) [unused when Furling=False] +---------------------- TOWER --------------------------------------------------- + 20 TwrNodes - Number of tower nodes used for analysis (-) +"NREL_5MW_Monopile_ElastoDyn_Tower.dat" TwrFile - Name of file containing tower properties (quoted string) +---------------------- OUTPUT -------------------------------------------------- +True SumPrint - Print summary data to ".sum" (flag) + 1 OutFile - Switch to determine where output will be placed: {1: in module output file only; 2: in glue code output file only; 3: both} (currently unused) +True TabDelim - Use tab delimiters in text tabular output file? (flag) (currently unused) +"ES10.3E2" OutFmt - Format used for text tabular output (except time). Resulting field should be 10 characters. (quoted string) (currently unused) + 0 TStart - Time to begin tabular output (s) (currently unused) + 1 DecFact - Decimation factor for tabular output {1: output every time step} (-) (currently unused) + 1 NTwGages - Number of tower nodes that have strain gages for output [0 to 9] (-) + 20 TwrGagNd - List of tower nodes that have strain gages [1 to TwrNodes] (-) [unused if NTwGages=0] + 3 NBlGages - Number of blade nodes that have strain gages for output [0 to 9] (-) + 5, 9, 13 BldGagNd - List of blade nodes that have strain gages [1 to BldNodes] (-) [unused if NBlGages=0] + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +"OoPDefl1, IPDefl1, TwstDefl1" - Blade 1 out-of-plane and in-plane deflections and tip twist +"BldPitch1" - Blade 1 pitch angle +"Azimuth" - Blade 1 azimuth angle +"RotSpeed, GenSpeed" - Low-speed shaft and high-speed shaft speeds +"TwHt1TPxi, TwHt1TPyi, TTDspTwst" - Tower fore-aft and side-to-side displacements and top twist +"PtfmSurge, PtfmSway" - Platform horizontal surge displacement +"PtfmRoll , PtfmPitch" - Platform rotational displacements +"Spn2MLxb1, Spn2MLyb1" - Blade 1 local edgewise and flapwise bending moments at span station 2 (approx. 50% span) +"RootFxc1, RootFyc1, RootFzc1" - Out-of-plane shear, in-plane shear, and axial forces at the root of blade 1 +"RootMxc1, RootMyc1, RootMzc1" - In-plane bending, out-of-plane bending, and pitching moments at the root of blade 1 +"RotTorq, LSSGagMya, LSSGagMza" - Rotor torque and low-speed shaft 0- and 90-bending moments at the main bearing +"YawBrFxp, YawBrFyp, YawBrFzp" - Fore-aft shear, side-to-side shear, and vertical forces at the top of the tower (not rotating with nacelle yaw) +"YawBrMxp, YawBrMyp, YawBrMzp" - Side-to-side bending, fore-aft bending, and yaw moments at the top of the tower (not rotating with nacelle yaw) +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +--------------------------------------------------------------------------------------- diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ElastoDyn_Tower.dat b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ElastoDyn_Tower.dat new file mode 100644 index 0000000..c29c6ef --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ElastoDyn_Tower.dat @@ -0,0 +1,54 @@ +------- ELASTODYN V1.00.* TOWER INPUT FILE ------------------------------------- +NREL 5.0 MW offshore baseline monopile tower for flexible monopile modeled in SubDyn. +---------------------- TOWER PARAMETERS ---------------------------------------- + 11 NTwInpSt - Number of input stations to specify tower geometry + 1.0 TwrFADmp(1) - Tower 1st fore-aft mode structural damping ratio (%) + 1.0 TwrFADmp(2) - Tower 2nd fore-aft mode structural damping ratio (%) + 1.0 TwrSSDmp(1) - Tower 1st side-to-side mode structural damping ratio (%) + 1.0 TwrSSDmp(2) - Tower 2nd side-to-side mode structural damping ratio (%) +---------------------- TOWER ADJUSTMUNT FACTORS -------------------------------- + 1.0 FAStTunr(1) - Tower fore-aft modal stiffness tuner, 1st mode (-) + 1.0 FAStTunr(2) - Tower fore-aft modal stiffness tuner, 2nd mode (-) + 1.0 SSStTunr(1) - Tower side-to-side stiffness tuner, 1st mode (-) + 1.0 SSStTunr(2) - Tower side-to-side stiffness tuner, 2nd mode (-) + 1.0 AdjTwMa - Factor to adjust tower mass density (-) + 1.0 AdjFASt - Factor to adjust tower fore-aft stiffness (-) + 1.0 AdjSSSt - Factor to adjust tower side-to-side stiffness (-) +---------------------- DISTRIBUTED TOWER PROPERTIES ---------------------------- +HtFract TMassDen TwFAStif TwSSStif + (-) (kg/m) (Nm^2) (Nm^2) +0.0 4.3065100E+03 4.7449000E+11 4.7449000E+11 +1.0E-01 4.0304400E+03 4.1308000E+11 4.1308000E+11 +2.0E-01 3.7634500E+03 3.5783000E+11 3.5783000E+11 +3.0E-01 3.5055200E+03 3.0830000E+11 3.0830000E+11 +4.0E-01 3.2566600E+03 2.6408000E+11 2.6408000E+11 +5.0E-01 3.0168600E+03 2.2480000E+11 2.2480000E+11 +6.0E-01 2.7861300E+03 1.9006000E+11 1.9006000E+11 +7.0E-01 2.5644600E+03 1.5949000E+11 1.5949000E+11 +8.0E-01 2.3518700E+03 1.3277000E+11 1.3277000E+11 +9.0E-01 2.1483400E+03 1.0954000E+11 1.0954000E+11 +1.0E+00 1.9538700E+03 8.9490000E+10 8.9490000E+10 +---------------------- TOWER FORE-AFT MODE SHAPES ------------------------------ + 0.9877 TwFAM1Sh(2) - Mode 1, coefficient of x^2 term + 0.1608 TwFAM1Sh(3) - , coefficient of x^3 term + -0.1884 TwFAM1Sh(4) - , coefficient of x^4 term + 0.1508 TwFAM1Sh(5) - , coefficient of x^5 term + -0.1108 TwFAM1Sh(6) - , coefficient of x^6 term + -1.0297 TwFAM2Sh(2) - Mode 2, coefficient of x^2 term + 1.4443 TwFAM2Sh(3) - , coefficient of x^3 term + 0.8883 TwFAM2Sh(4) - , coefficient of x^4 term + -0.1276 TwFAM2Sh(5) - , coefficient of x^5 term + -0.1752 TwFAM2Sh(6) - , coefficient of x^6 term +---------------------- TOWER SIDE-TO-SIDE MODE SHAPES -------------------------- + 0.9792 TwSSM1Sh(2) - Mode 1, coefficient of x^2 term + 0.1618 TwSSM1Sh(3) - , coefficient of x^3 term + -0.1797 TwSSM1Sh(4) - , coefficient of x^4 term + 0.1453 TwSSM1Sh(5) - , coefficient of x^5 term + -0.1065 TwSSM1Sh(6) - , coefficient of x^6 term + -1.2253 TwSSM2Sh(2) - Mode 2, coefficient of x^2 term + 1.3297 TwSSM2Sh(3) - , coefficient of x^3 term + 1.0340 TwSSM2Sh(4) - , coefficient of x^4 term + -0.1508 TwSSM2Sh(5) - , coefficient of x^5 term + 0.0123 TwSSM2Sh(6) - , coefficient of x^6 term + + diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_HydroDyn.dat b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_HydroDyn.dat new file mode 100644 index 0000000..32a8f2d --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_HydroDyn.dat @@ -0,0 +1,151 @@ +------- HydroDyn v2.03.* Input File -------------------------------------------- +NREL 5.0 MW offshore baseline floating platform input properties for the OC3 Monopile. +False Echo - Echo the input file data (flag) +---------------------- ENVIRONMENTAL CONDITIONS -------------------------------- + "default" WtrDens - Water density (kg/m^3) + "default" WtrDpth - Water depth (meters) + "default" MSL2SWL - Offset between still-water level and mean sea level (meters) [positive upward; unused when WaveMod = 6; must be zero if PotMod=1 or 2] +---------------------- WAVES --------------------------------------------------- + 2 WaveMod - Incident wave kinematics model {0: none=still water, 1: regular (periodic), 1P#: regular with user-specified phase, 2: JONSWAP/Pierson-Moskowitz spectrum (irregular), 3: White noise spectrum (irregular), 4: user-defined spectrum from routine UserWaveSpctrm (irregular), 5: Externally generated wave-elevation time series, 6: Externally generated full wave-kinematics time series [option 6 is invalid for PotMod/=0]} (switch) + 0 WaveStMod - Model for stretching incident wave kinematics to instantaneous free surface {0: none=no stretching, 1: vertical stretching, 2: extrapolation stretching, 3: Wheeler stretching} (switch) [unused when WaveMod=0 or when PotMod/=0] + 3630 WaveTMax - Analysis time for incident wave calculations (sec) [unused when WaveMod=0; determines WaveDOmega=2Pi/WaveTMax in the IFFT] + 0.25 WaveDT - Time step for incident wave calculations (sec) [unused when WaveMod=0; 0.1<=WaveDT<=1.0 recommended; determines WaveOmegaMax=Pi/WaveDT in the IFFT] + 6 WaveHs - Significant wave height of incident waves (meters) [used only when WaveMod=1, 2, or 3] + 10 WaveTp - Peak-spectral period of incident waves (sec) [used only when WaveMod=1 or 2] +"DEFAULT" WavePkShp - Peak-shape parameter of incident wave spectrum (-) or DEFAULT (string) [used only when WaveMod=2; use 1.0 for Pierson-Moskowitz] + 0.15708 WvLowCOff - Low cut-off frequency or lower frequency limit of the wave spectrum beyond which the wave spectrum is zeroed (rad/s) [unused when WaveMod=0, 1, or 6] + 3.2 WvHiCOff - High cut-off frequency or upper frequency limit of the wave spectrum beyond which the wave spectrum is zeroed (rad/s) [unused when WaveMod=0, 1, or 6] + 0 WaveDir - Incident wave propagation heading direction (degrees) [unused when WaveMod=0 or 6] + 0 WaveDirMod - Directional spreading function {0: none, 1: COS2S} (-) [only used when WaveMod=2,3, or 4] + 1 WaveDirSpread - Wave direction spreading coefficient ( > 0 ) (-) [only used when WaveMod=2,3, or 4 and WaveDirMod=1] + 1 WaveNDir - Number of wave directions (-) [only used when WaveMod=2,3, or 4 and WaveDirMod=1; odd number only] + 90 WaveDirRange - Range of wave directions (full range: WaveDir +/- 1/2*WaveDirRange) (degrees) [only used when WaveMod=2,3,or 4 and WaveDirMod=1] + 123456789 WaveSeed(1) - First random seed of incident waves [-2147483648 to 2147483647] (-) [unused when WaveMod=0, 5, or 6] + RANLUX WaveSeed(2) - Second random seed of incident waves [-2147483648 to 2147483647] for intrinsic pRNG, or an alternative pRNG: "RanLux" (-) [unused when WaveMod=0, 5, or 6] +TRUE WaveNDAmp - Flag for normally distributed amplitudes (flag) [only used when WaveMod=2, 3, or 4] +"" WvKinFile - Root name of externally generated wave data file(s) (quoted string) [used only when WaveMod=5 or 6] + 1 NWaveElev - Number of points where the incident wave elevations can be computed (-) [maximum of 9 output locations] + 0 WaveElevxi - List of xi-coordinates for points where the incident wave elevations can be output (meters) [NWaveElev points, separated by commas or white space; usused if NWaveElev = 0] + 0 WaveElevyi - List of yi-coordinates for points where the incident wave elevations can be output (meters) [NWaveElev points, separated by commas or white space; usused if NWaveElev = 0] +---------------------- 2ND-ORDER WAVES ----------------------------------------- [unused with WaveMod=0 or 6] +True WvDiffQTF - Full difference-frequency 2nd-order wave kinematics (flag) +True WvSumQTF - Full summation-frequency 2nd-order wave kinematics (flag) + 0 WvLowCOffD - Low frequency cutoff used in the difference-frequencies (rad/s) [Only used with a difference-frequency method] + 3.04292 WvHiCOffD - High frequency cutoff used in the difference-frequencies (rad/s) [Only used with a difference-frequency method] + 0.314159 WvLowCOffS - Low frequency cutoff used in the summation-frequencies (rad/s) [Only used with a summation-frequency method] + 3.2 WvHiCOffS - High frequency cutoff used in the summation-frequencies (rad/s) [Only used with a summation-frequency method] +---------------------- CURRENT ------------------------------------------------- [unused with WaveMod=6] + 0 CurrMod - Current profile model {0: none=no current, 1: standard, 2: user-defined from routine UserCurrent} (switch) + 0 CurrSSV0 - Sub-surface current velocity at still water level (m/s) [used only when CurrMod=1] +"DEFAULT" CurrSSDir - Sub-surface current heading direction (degrees) or DEFAULT (string) [used only when CurrMod=1] + 20 CurrNSRef - Near-surface current reference depth (meters) [used only when CurrMod=1] + 0 CurrNSV0 - Near-surface current velocity at still water level (m/s) [used only when CurrMod=1] + 0 CurrNSDir - Near-surface current heading direction (degrees) [used only when CurrMod=1] + 0 CurrDIV - Depth-independent current velocity (m/s) [used only when CurrMod=1] + 0 CurrDIDir - Depth-independent current heading direction (degrees) [used only when CurrMod=1] +---------------------- FLOATING PLATFORM --------------------------------------- [unused with WaveMod=6] + 0 PotMod - Potential-flow model {0: none=no potential flow, 1: frequency-to-time-domain transforms based on WAMIT output, 2: fluid-impulse theory (FIT)} (switch) + 1 ExctnMod - Wave-excitation model {0: no wave-excitation calculation, 1: DFT, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ssexctn INPUT FILE] + 0 RdtnMod - Radiation memory-effect model {0: no memory-effect calculation, 1: convolution, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ss INPUT FILE] + 60 RdtnTMax - Analysis time for wave radiation kernel calculations (sec) [only used when PotMod=1 and RdtnMod>0; determines RdtnDOmega=Pi/RdtnTMax in the cosine transform; MAKE SURE THIS IS LONG ENOUGH FOR THE RADIATION IMPULSE RESPONSE FUNCTIONS TO DECAY TO NEAR-ZERO FOR THE GIVEN PLATFORM!] + 0.0125 RdtnDT - Time step for wave radiation kernel calculations (sec) [only used when PotMod=1 and ExctnMod>0 or RdtnMod>0; DT<=RdtnDT<=0.1 recommended; determines RdtnOmegaMax=Pi/RdtnDT in the cosine transform] + 1 NBody - Number of WAMIT bodies to be used (-) [>=1; only used when PotMod=1. If NBodyMod=1, the WAMIT data contains a vector of size 6*NBody x 1 and matrices of size 6*NBody x 6*NBody; if NBodyMod>1, there are NBody sets of WAMIT data each with a vector of size 6 x 1 and matrices of size 6 x 6] + 1 NBodyMod - Body coupling model {1: include coupling terms between each body and NBody in HydroDyn equals NBODY in WAMIT, 2: neglect coupling terms between each body and NBODY=1 with XBODY=0 in WAMIT, 3: Neglect coupling terms between each body and NBODY=1 with XBODY=/0 in WAMIT} (switch) [only used when PotMod=1] +"unused" PotFile - Root name of potential-flow model data; WAMIT output files containing the linear, nondimensionalized, hydrostatic restoring matrix (.hst), frequency-dependent hydrodynamic added mass matrix and damping matrix (.1), and frequency- and direction-dependent wave excitation force vector per unit wave amplitude (.3) (quoted string) [1 to NBody if NBodyMod>1] [MAKE SURE THE FREQUENCIES INHERENT IN THESE WAMIT FILES SPAN THE PHYSICALLY-SIGNIFICANT RANGE OF FREQUENCIES FOR THE GIVEN PLATFORM; THEY MUST CONTAIN THE ZERO- AND INFINITE-FREQUENCY LIMITS!] + 1 WAMITULEN - Characteristic body length scale used to redimensionalize WAMIT output (meters) [1 to NBody if NBodyMod>1] [only used when PotMod=1] + 0.0 PtfmRefxt - The xt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1] + 0.0 PtfmRefyt - The yt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1] + 0.0 PtfmRefzt - The zt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1. If NBodyMod=2,PtfmRefzt=0.0] + 0.0 PtfmRefztRot - The rotation about zt of the body reference frame(s) from xt/yt (degrees) [1 to NBody] [only used when PotMod=1] + 0 PtfmVol0 - Displaced volume of water when the body is in its undisplaced position (m^3) [1 to NBody] [only used when PotMod=1; USE THE SAME VALUE COMPUTED BY WAMIT AS OUTPUT IN THE .OUT FILE!] + 0.0 PtfmCOBxt - The xt offset of the center of buoyancy (COB) from (0,0) (meters) [1 to NBody] [only used when PotMod=1] + 0.0 PtfmCOByt - The yt offset of the center of buoyancy (COB) from (0,0) (meters) [1 to NBody] [only used when PotMod=1] +---------------------- 2ND-ORDER FLOATING PLATFORM FORCES ---------------------- [unused with WaveMod=0 or 6, or PotMod=0 or 2] + 0 MnDrift - Mean-drift 2nd-order forces computed {0: None; [7, 8, 9, 10, 11, or 12]: WAMIT file to use} [Only one of MnDrift, NewmanApp, or DiffQTF can be non-zero. If NBody>1, MnDrift /=8] + 0 NewmanApp - Mean- and slow-drift 2nd-order forces computed with Newman's approximation {0: None; [7, 8, 9, 10, 11, or 12]: WAMIT file to use} [Only one of MnDrift, NewmanApp, or DiffQTF can be non-zero. If NBody>1, NewmanApp/=8. Used only when WaveDirMod=0] + 0 DiffQTF - Full difference-frequency 2nd-order forces computed with full QTF {0: None; [10, 11, or 12]: WAMIT file to use} [Only one of MnDrift, NewmanApp, or DiffQTF can be non-zero] + 0 SumQTF - Full summation -frequency 2nd-order forces computed with full QTF {0: None; [10, 11, or 12]: WAMIT file to use} +---------------------- PLATFORM ADDITIONAL STIFFNESS AND DAMPING -------------- [unused with PotMod=0 or 2] + 0 AddF0 - Additional preload (N, N-m) [If NBodyMod=1, one size 6*NBody x 1 vector; if NBodyMod>1, NBody size 6 x 1 vectors] + 0 + 0 + 0 + 0 + 0 + 0 0 0 0 0 0 AddCLin - Additional linear stiffness (N/m, N/rad, N-m/m, N-m/rad) [If NBodyMod=1, one size 6*NBody x 6*NBody matrix; if NBodyMod>1, NBody size 6 x 6 matrices] + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 AddBLin - Additional linear damping(N/(m/s), N/(rad/s), N-m/(m/s), N-m/(rad/s)) [If NBodyMod=1, one size 6*NBody x 6*NBody matrix; if NBodyMod>1, NBody size 6 x 6 matrices] + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 AddBQuad - Additional quadratic drag(N/(m/s)^2, N/(rad/s)^2, N-m(m/s)^2, N-m/(rad/s)^2) [If NBodyMod=1, one size 6*NBody x 6*NBody matrix; if NBodyMod>1, NBody size 6 x 6 matrices] + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 + 0 0 0 0 0 0 +---------------------- AXIAL COEFFICIENTS -------------------------------------- + 1 NAxCoef - Number of axial coefficients (-) +AxCoefID AxCd AxCa AxCp + (-) (-) (-) (-) + 1 0.00 0.00 1.00 +---------------------- MEMBER JOINTS ------------------------------------------- + 2 NJoints - Number of joints (-) [must be exactly 0 or at least 2] +JointID Jointxi Jointyi Jointzi JointAxID JointOvrlp [JointOvrlp= 0: do nothing at joint, 1: eliminate overlaps by calculating super member] + (-) (m) (m) (m) (-) (switch) + 1 0.00000 0.00000 -20.00010 1 0 + 2 0.00000 0.00000 10.00000 1 0 +---------------------- MEMBER CROSS-SECTION PROPERTIES ------------------------- + 1 NPropSets - Number of member property sets (-) +PropSetID PropD PropThck + (-) (m) (m) + 1 6.00000 0.06000 +---------------------- SIMPLE HYDRODYNAMIC COEFFICIENTS (model 1) -------------- + SimplCd SimplCdMG SimplCa SimplCaMG SimplCp SimplCpMG SimplAxCd SimplAxCdMG SimplAxCa SimplAxCaMG SimplAxCp SimplAxCpMG + (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) + 1.00 1.00 1.00 1.00 1.00 1.00 1.00 0.00 0.00 1.00 1.00 1.00 +---------------------- DEPTH-BASED HYDRODYNAMIC COEFFICIENTS (model 2) --------- + 0 NCoefDpth - Number of depth-dependent coefficients (-) +Dpth DpthCd DpthCdMG DpthCa DpthCaMG DpthCp DpthCpMG DpthAxCd DpthAxCdMG DpthAxCa DpthAxCaMG DpthAxCp DpthAxCpMG +(m) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) +---------------------- MEMBER-BASED HYDRODYNAMIC COEFFICIENTS (model 3) -------- + 0 NCoefMembers - Number of member-based coefficients (-) +MemberID MemberCd1 MemberCd2 MemberCdMG1 MemberCdMG2 MemberCa1 MemberCa2 MemberCaMG1 MemberCaMG2 MemberCp1 MemberCp2 MemberCpMG1 MemberCpMG2 MemberAxCd1 MemberAxCd2 MemberAxCdMG1 MemberAxCdMG2 MemberAxCa1 MemberAxCa2 MemberAxCaMG1 MemberAxCaMG2 MemberAxCp1 MemberAxCp2 MemberAxCpMG1 MemberAxCpMG2 + (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) +-------------------- MEMBERS ------------------------------------------------- + 1 NMembers - Number of members (-) +MemberID MJointID1 MJointID2 MPropSetID1 MPropSetID2 MDivSize MCoefMod PropPot [MCoefMod=1: use simple coeff table, 2: use depth-based coeff table, 3: use member-based coeff table] [ PropPot/=0 if member is modeled with potential-flow theory] + (-) (-) (-) (-) (-) (m) (switch) (flag) + 1 1 2 1 1 0.5000 1 FALSE +---------------------- FILLED MEMBERS ------------------------------------------ + 0 NFillGroups - Number of filled member groups (-) [If FillDens = DEFAULT, then FillDens = WtrDens; FillFSLoc is related to MSL2SWL] +FillNumM FillMList FillFSLoc FillDens +(-) (-) (m) (kg/m^3) +---------------------- MARINE GROWTH ------------------------------------------- + 0 NMGDepths - Number of marine-growth depths specified (-) +MGDpth MGThck MGDens +(m) (m) (kg/m^3) +---------------------- MEMBER OUTPUT LIST -------------------------------------- + 0 NMOutputs - Number of member outputs (-) [must be <= 99] +MemberID NOutLoc NodeLocs [NOutLoc < 10; node locations are normalized distance from the start of the member, and must be >=0 and <= 1] [unused if NMOutputs=0] + (-) (-) (-) +---------------------- JOINT OUTPUT LIST --------------------------------------- + 0 NJOutputs - Number of joint outputs [Must be < 10] + 0 JOutLst - List of JointIDs which are to be output (-)[unused if NJOutputs=0] +---------------------- OUTPUT -------------------------------------------------- +True HDSum - Output a summary file [flag] +False OutAll - Output all user-specified member and joint loads (only at each member end, not interior locations) [flag] + 2 OutSwtch - Output requested channels to: [1=Hydrodyn.out, 2=GlueCode.out, 3=both files] +"ES11.4e2" OutFmt - Output format for numerical results (quoted string) [not checked for validity!] +"A11" OutSFmt - Output format for header strings (quoted string) [not checked for validity!] +---------------------- OUTPUT CHANNELS ----------------------------------------- +"Wave1Elev" - Wave elevation at the WAMIT reference point (0,0) +"HydroFxi, HydroFyi, HydroFzi" +"HydroMxi, HydroMyi, HydroMzi" +END of output channels and end of file. (the word "END" must appear in the first 3 columns of this line) diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ServoDyn.dat b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ServoDyn.dat new file mode 100644 index 0000000..32eb389 --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_ServoDyn.dat @@ -0,0 +1,110 @@ +------- SERVODYN v1.05.* INPUT FILE -------------------------------------------- +NREL 5.0 MW Baseline Wind Turbine for Use in Offshore Analysis. Properties from Dutch Offshore Wind Energy Converter (DOWEC) 6MW Pre-Design (10046_009.pdf) and REpower 5M 5MW (5m_uk.pdf); +---------------------- SIMULATION CONTROL -------------------------------------- +False Echo - Echo input data to .ech (flag) +"default" DT - Communication interval for controllers (s) (or "default") +---------------------- PITCH CONTROL ------------------------------------------- + 5 PCMode - Pitch control mode {0: none, 3: user-defined from routine PitchCntrl, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch) + 0 TPCOn - Time to enable active pitch control (s) [unused when PCMode=0] + 9999.9 TPitManS(1) - Time to start override pitch maneuver for blade 1 and end standard pitch control (s) + 9999.9 TPitManS(2) - Time to start override pitch maneuver for blade 2 and end standard pitch control (s) + 9999.9 TPitManS(3) - Time to start override pitch maneuver for blade 3 and end standard pitch control (s) [unused for 2 blades] + 2 PitManRat(1) - Pitch rate at which override pitch maneuver heads toward final pitch angle for blade 1 (deg/s) + 2 PitManRat(2) - Pitch rate at which override pitch maneuver heads toward final pitch angle for blade 2 (deg/s) + 2 PitManRat(3) - Pitch rate at which override pitch maneuver heads toward final pitch angle for blade 3 (deg/s) [unused for 2 blades] + 0 BlPitchF(1) - Blade 1 final pitch for pitch maneuvers (degrees) + 0 BlPitchF(2) - Blade 2 final pitch for pitch maneuvers (degrees) + 0 BlPitchF(3) - Blade 3 final pitch for pitch maneuvers (degrees) [unused for 2 blades] +---------------------- GENERATOR AND TORQUE CONTROL ---------------------------- + 5 VSContrl - Variable-speed control mode {0: none, 1: simple VS, 3: user-defined from routine UserVSCont, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch) + 2 GenModel - Generator model {1: simple, 2: Thevenin, 3: user-defined from routine UserGen} (switch) [used only when VSContrl=0] + 94.4 GenEff - Generator efficiency [ignored by the Thevenin and user-defined generator models] (%) +True GenTiStr - Method to start the generator {T: timed using TimGenOn, F: generator speed using SpdGenOn} (flag) +True GenTiStp - Method to stop the generator {T: timed using TimGenOf, F: when generator power = 0} (flag) + 9999.9 SpdGenOn - Generator speed to turn on the generator for a startup (HSS speed) (rpm) [used only when GenTiStr=False] + 0 TimGenOn - Time to turn on the generator for a startup (s) [used only when GenTiStr=True] + 9999.9 TimGenOf - Time to turn off the generator (s) [used only when GenTiStp=True] +---------------------- SIMPLE VARIABLE-SPEED TORQUE CONTROL -------------------- + 9999.9 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1] + 9999.9 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1] + 9999.9 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1] + 9999.9 VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1] +---------------------- SIMPLE INDUCTION GENERATOR ------------------------------ + 9999.9 SIG_SlPc - Rated generator slip percentage (%) [used only when VSContrl=0 and GenModel=1] + 9999.9 SIG_SySp - Synchronous (zero-torque) generator speed (rpm) [used only when VSContrl=0 and GenModel=1] + 9999.9 SIG_RtTq - Rated torque (N-m) [used only when VSContrl=0 and GenModel=1] + 9999.9 SIG_PORt - Pull-out ratio (Tpullout/Trated) (-) [used only when VSContrl=0 and GenModel=1] +---------------------- THEVENIN-EQUIVALENT INDUCTION GENERATOR ----------------- + 9999.9 TEC_Freq - Line frequency [50 or 60] (Hz) [used only when VSContrl=0 and GenModel=2] + 9998 TEC_NPol - Number of poles [even integer > 0] (-) [used only when VSContrl=0 and GenModel=2] + 9999.9 TEC_SRes - Stator resistance (ohms) [used only when VSContrl=0 and GenModel=2] + 9999.9 TEC_RRes - Rotor resistance (ohms) [used only when VSContrl=0 and GenModel=2] + 9999.9 TEC_VLL - Line-to-line RMS voltage (volts) [used only when VSContrl=0 and GenModel=2] + 9999.9 TEC_SLR - Stator leakage reactance (ohms) [used only when VSContrl=0 and GenModel=2] + 9999.9 TEC_RLR - Rotor leakage reactance (ohms) [used only when VSContrl=0 and GenModel=2] + 9999.9 TEC_MR - Magnetizing reactance (ohms) [used only when VSContrl=0 and GenModel=2] +---------------------- HIGH-SPEED SHAFT BRAKE ---------------------------------- + 0 HSSBrMode - HSS brake model {0: none, 1: simple, 3: user-defined from routine UserHSSBr, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch) + 9999.9 THSSBrDp - Time to initiate deployment of the HSS brake (s) + 0.6 HSSBrDT - Time for HSS-brake to reach full deployment once initiated (sec) [used only when HSSBrMode=1] + 28116.2 HSSBrTqF - Fully deployed HSS-brake torque (N-m) +---------------------- NACELLE-YAW CONTROL ------------------------------------- + 0 YCMode - Yaw control mode {0: none, 3: user-defined from routine UserYawCont, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch) + 9999.9 TYCOn - Time to enable active yaw control (s) [unused when YCMode=0] + 0 YawNeut - Neutral yaw position--yaw spring force is zero at this yaw (degrees) +9.02832E+09 YawSpr - Nacelle-yaw spring constant (N-m/rad) + 1.916E+07 YawDamp - Nacelle-yaw damping constant (N-m/(rad/s)) + 9999.9 TYawManS - Time to start override yaw maneuver and end standard yaw control (s) + 2 YawManRat - Yaw maneuver rate (in absolute value) (deg/s) + 0 NacYawF - Final yaw angle for override yaw maneuvers (degrees) +---------------------- AERODYNAMIC FLOW CONTROL -------------------------------- + 0 AfCmode - Airfoil control mode {0: none, 1: cosine wave cycle, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch) + 0 AfC_Mean - Mean level for cosine cycling or steady value (-) [used only with AfCmode==1] + 0 AfC_Amp - Amplitude for for cosine cycling of flap signal (-) [used only with AfCmode==1] + 0 AfC_Phase - Phase relative to the blade azimuth (0 is vertical) for for cosine cycling of flap signal (deg) [used only with AfCmode==1] +---------------------- STRUCTURAL CONTROL -------------------------------------- +0 NumBStC - Number of blade structural controllers (integer) +"unused" BStCfiles - Name of the files for blade structural controllers (quoted strings) [unused when NumBStC==0] +0 NumNStC - Number of nacelle structural controllers (integer) +"unused" NStCfiles - Name of the files for nacelle structural controllers (quoted strings) [unused when NumNStC==0] +0 NumTStC - Number of tower structural controllers (integer) +"unused" TStCfiles - Name of the files for tower structural controllers (quoted strings) [unused when NumTStC==0] +0 NumSStC - Number of substructure structural controllers (integer) +"unused" SStCfiles - Name of the files for substructure structural controllers (quoted strings) [unused when NumSStC==0] +---------------------- CABLE CONTROL ------------------------------------------- + 0 CCmode - Cable control mode {0: none, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch) +---------------------- BLADED INTERFACE ---------------------------------------- [used only with Bladed Interface] +"../5MW_Baseline/ServoData/DISCON.dll" DLL_FileName - Name/location of the dynamic library {.dll [Windows] or .so [Linux]} in the Bladed-DLL format (-) [used only with Bladed Interface] +"DISCON.IN" DLL_InFile - Name of input file sent to the DLL (-) [used only with Bladed Interface] +"DISCON" DLL_ProcName - Name of procedure in DLL to be called (-) [case sensitive; used only with DLL Interface] +"default" DLL_DT - Communication interval for dynamic library (s) (or "default") [used only with Bladed Interface] +false DLL_Ramp - Whether a linear ramp should be used between DLL_DT time steps [introduces time shift when true] (flag) [used only with Bladed Interface] + 9999.9 BPCutoff - Cutoff frequency for low-pass filter on blade pitch from DLL (Hz) [used only with Bladed Interface] + 0 NacYaw_North - Reference yaw angle of the nacelle when the upwind end points due North (deg) [used only with Bladed Interface] + 0 Ptch_Cntrl - Record 28: Use individual pitch control {0: collective pitch; 1: individual pitch control} (switch) [used only with Bladed Interface] + 0 Ptch_SetPnt - Record 5: Below-rated pitch angle set-point (deg) [used only with Bladed Interface] + 0 Ptch_Min - Record 6: Minimum pitch angle (deg) [used only with Bladed Interface] + 0 Ptch_Max - Record 7: Maximum pitch angle (deg) [used only with Bladed Interface] + 0 PtchRate_Min - Record 8: Minimum pitch rate (most negative value allowed) (deg/s) [used only with Bladed Interface] + 0 PtchRate_Max - Record 9: Maximum pitch rate (deg/s) [used only with Bladed Interface] + 0 Gain_OM - Record 16: Optimal mode gain (Nm/(rad/s)^2) [used only with Bladed Interface] + 0 GenSpd_MinOM - Record 17: Minimum generator speed (rpm) [used only with Bladed Interface] + 0 GenSpd_MaxOM - Record 18: Optimal mode maximum speed (rpm) [used only with Bladed Interface] + 0 GenSpd_Dem - Record 19: Demanded generator speed above rated (rpm) [used only with Bladed Interface] + 0 GenTrq_Dem - Record 22: Demanded generator torque above rated (Nm) [used only with Bladed Interface] + 0 GenPwr_Dem - Record 13: Demanded power (W) [used only with Bladed Interface] +---------------------- BLADED INTERFACE TORQUE-SPEED LOOK-UP TABLE ------------- + 0 DLL_NumTrq - Record 26: No. of points in torque-speed look-up table {0 = none and use the optimal mode parameters; nonzero = ignore the optimal mode PARAMETERs by setting Record 16 to 0.0} (-) [used only with Bladed Interface] + GenSpd_TLU GenTrq_TLU + (rpm) (Nm) +---------------------- OUTPUT -------------------------------------------------- +True SumPrint - Print summary data to .sum (flag) (currently unused) + 1 OutFile - Switch to determine where output will be placed: {1: in module output file only; 2: in glue code output file only; 3: both} (currently unused) +True TabDelim - Use tab delimiters in text tabular output file? (flag) (currently unused) +"ES10.3E2" OutFmt - Format used for text tabular output (except time). Resulting field should be 10 characters. (quoted string) (currently unused) + 30 TStart - Time to begin tabular output (s) (currently unused) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +"GenPwr" - Electrical generator power and torque +"GenTq" - Electrical generator power and torque +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +--------------------------------------------------------------------------------------- diff --git a/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_SubDyn.dat b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_SubDyn.dat new file mode 100644 index 0000000..ffddad0 --- /dev/null +++ b/examples/NREL_5MW_Monopile/NREL_5MW_Monopile_SubDyn.dat @@ -0,0 +1,99 @@ +----------- SubDyn MultiMember Support Structure Input File --------------------------- +OC3 Monopile configuration (pile only). +-------------------------- SIMULATION CONTROL ----------------------------------------- +False Echo - Echo input data to ".SD.ech" (flag) +"DEFAULT" SDdeltaT - Local Integration Step. If "default", the glue-code integration step will be used. + 3 IntMethod - Integration Method [1/2/3/4 = RK4/AB4/ABM4/AM2]. +True SttcSolve - Solve dynamics about static equilibrium point +False GuyanLoadCorrection - Include extra moment from lever arm at interface and rotate FEM for floating. +-------------------- FEA and CRAIG-BAMPTON PARAMETERS --------------------------------- + 3 FEMMod - FEM switch: element model in the FEM. [1= Euler-Bernoulli(E-B); 2=Tapered E-B (unavailable); 3= 2-node Timoshenko; 4= 2-node tapered Timoshenko (unavailable)] + 3 NDiv - Number of sub-elements per member +True CBMod - [T/F] If True perform C-B reduction, else full FEM dofs will be retained. If True, select Nmodes to retain in C-B reduced system. + 0 Nmodes - Number of internal modes to retain (ignored if CBMod=False). If Nmodes=0 --> Guyan Reduction. + 1 JDampings - Damping Ratios for each retained mode (% of critical) If Nmodes>0, list Nmodes structural damping ratios for each retained mode (% of critical), or a single damping ratio to be applied to all retained modes. (last entered value will be used for all remaining modes). + 2 GuyanDampMod - Guyan damping {0=none, 1=Rayleigh Damping, 2=user specified 6x6 matrix} + 0.000, 0.000 RayleighDamp - Mass and stiffness proportional damping coefficients (Rayleigh Damping) [only if GuyanDampMod=1] + 6 GuyanDampSize - Guyan damping matrix (6x6) [only if GuyanDampMod=2] + 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 + 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 + 0.0000e+00 0.0000e+00 1.4625e+06 0.0000e+00 0.0000e+00 0.0000e+00 + 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 + 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 + 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 0.0000e+00 +---- STRUCTURE JOINTS: joints connect structure members (~Hydrodyn Input File) -------- + 4 NJoints - Number of joints (-) +JointID JointXss JointYss JointZss JointType JointDirX JointDirY JointDirZ JointStiff ![Coordinates of Member joints in SS-Coordinate System][JointType={1:cantilever, 2:universal joint, 3:revolute joint, 4:spherical joint}] + (-) (m) (m) (m) (-) (-) (-) (-) (Nm/rad) + 1 0.00000 0.00000 -20.00010 1 0.0 0.0 0.0 0.0 + 2 0.00000 0.00000 -10.00000 1 0.0 0.0 0.0 0.0 + 3 0.00000 0.00000 0.00000 1 0.0 0.0 0.0 0.0 + 4 0.00000 0.00000 10.00000 1 0.0 0.0 0.0 0.0 +------------------- BASE REACTION JOINTS: 1/0 for Locked/Free DOF @ each Reaction Node --------------------- + 1 NReact - Number of Joints with reaction forces; be sure to remove all rigid motion DOFs of the structure (else det([K])=[0]) +RJointID RctTDXss RctTDYss RctTDZss RctRDXss RctRDYss RctRDZss SSIfile ![Global Coordinate System] + (-) (flag) (flag) (flag) (flag) (flag) (flag) (string) + 1 1 1 1 1 1 1 "" +------- INTERFACE JOINTS: 1/0 for Locked (to the TP)/Free DOF @each Interface Joint (only Locked-to-TP implemented thus far (=rigid TP)) --------- + 1 NInterf - Number of interface joints locked to the Transition Piece (TP): be sure to remove all rigid motion dofs +IJointID ItfTDXss ItfTDYss ItfTDZss ItfRDXss ItfRDYss ItfRDZss ![Global Coordinate System] + (-) (flag) (flag) (flag) (flag) (flag) (flag) + 4 1 1 1 1 1 1 +----------------------------------- MEMBERS ------------------------------------------- + 3 NMembers - Number of members (-) +MemberID MJointID1 MJointID2 MPropSetID1 MPropSetID2 MType COSMID ![MType={1:beam circ., 2:cable, 3:rigid, 4:beam arb.}. COMSID={-1:none}] + (-) (-) (-) (-) (-) (-) (-) + 1 1 2 1 1 1 -1 + 2 2 3 1 1 1 -1 + 3 3 4 1 1 1 -1 +------------------ CIRCULAR BEAM CROSS-SECTION PROPERTIES ----------------------------- + 4 NPropSets - Number of structurally unique cross-sections +PropSetID YoungE ShearG MatDens XsecD XsecT + (-) (N/m2) (N/m2) (kg/m3) (m) (m) + 1 2.10000e+11 8.08000e+10 8500.00 6.000000 0.060000 + 2 2.10000e+11 8.08000e+10 8500.00 6.000000 0.027000 + 3 2.10000e+11 8.08000e+10 8500.00 3.870000 0.019000 + 4 2.10000e+14 8.08000e+14 1.00 1.000000 0.010000 +----------------- ARBITRARY BEAM CROSS-SECTION PROPERTIES ----------------------------- + 0 NXPropSets - Number of structurally unique non-circular cross-sections (if 0 the following table is ignored) +PropSetID YoungE ShearG MatDens XsecA XsecAsx XsecAsy XsecJxx XsecJyy XsecJ0 + (-) (N/m2) (N/m2) (kg/m3) (m2) (m2) (m2) (m4) (m4) (m4) +-------------------------- CABLE PROPERTIES ------------------------------------------- + 0 NCablePropSets - Number of cable cable properties +PropSetID EA MatDens T0 CtrlChannel + (-) (N) (kg/m) (N) (-) +----------------------- RIGID LINK PROPERTIES ----------------------------------------- + 0 NRigidPropSets - Number of rigid link properties +PropSetID MatDens + (-) (kg/m) +---------------------- MEMBER COSINE MATRICES COSM(i,j) ------------------------------- + 0 NCOSMs - Number of unique cosine matrices (i.e., of unique member alignments including principal axis rotations); ignored if NXPropSets=0 or 9999 in any element below +COSMID COSM11 COSM12 COSM13 COSM21 COSM22 COSM23 COSM31 COSM32 COSM33 + (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) +------------------------ JOINT ADDITIONAL CONCENTRATED MASSES-------------------------- + 0 NCmass - Number of joints with concentrated masses; Global Coordinate System +CMJointID JMass JMXX JMYY JMZZ JMXY JMXZ JMYZ MCGX MCGY MCGZ + (-) (kg) (kg*m^2) (kg*m^2) (kg*m^2) (kg*m^2) (kg*m^2) (kg*m^2) (m) (m) (m) +---------------------------- OUTPUT: SUMMARY & OUTFILE -------------------------------- +True SumPrint - Output a Summary File (flag) +0 OutCBModes - Output Guyan and Craig-Bampton modes {0: No output, 1: JSON output}, (flag) +0 OutFEMModes - Output first 30 FEM modes {0: No output, 1: JSON output} (flag) +False OutCOSM - Output cosine matrices with the selected output member forces (flag) +False OutAll - [T/F] Output all members' end forces + 2 OutSwtch - [1/2/3] Output requested channels to: 1=.SD.out; 2=.out (generated by FAST); 3=both files. +True TabDelim - Generate a tab-delimited output in the .SD.out file + 1 OutDec - Decimation of output in the .SD.out file +"ES11.4e2" OutFmt - Output format for numerical results in the .SD.out file +"A11" OutSFmt - Output format for header strings in the .SD.out file +------------------------- MEMBER OUTPUT LIST ------------------------------------------ + 2 NMOutputs - Number of members whose forces/displacements/velocities/accelerations will be output (-) [Must be <= 99]. +MemberID NOutCnt NodeCnt ![NOutCnt=how many nodes to get output for [< 10]; NodeCnt are local ordinal numbers from the start of the member, and must be >=1 and <= NDiv+1] If NMOutputs=0 leave blank as well. + (-) (-) (-) + 2 1 1 + 3 1 1 +------------------------- SSOutList: The next line(s) contains a list of output parameters that will be output in .SD.out or .out. ------ +"M2N1MKxe, M2N1MKye" - The local side-to-side and fore-aft bending moments at node 1 of member 3 (located at 0 m, i.e. MSL). +"M1N1MKxe, M1N1MKye" - The local side-to-side and fore-aft bending moments at node 1 of member 2 (located at -10 m, i.e. half way between MSL and mudline). +"-ReactFXss, -ReactFYss, -ReactFZss" - Base reactions: fore-aft shear, side-to-side shear and vertical forces at the mudline. +"-ReactMXss, -ReactMYss, -ReactMZss" - Base reactions: side-to-side, fore-aft and yaw moments at the mudline. +END of output channels and end of file. (the word "END" must appear in the first 3 columns of this line)