fix customprofile and add tutorial on it

bladex/__init__.py

@@ -1,16 +1,18 @@
 """
 BladeX init
 """
-__all__ = ['profilebase', 'nacaprofile', 'customprofile', 'reversepropeller', 'blade', 'shaft', 'propeller', 'deform', 'params', 'ndinterpolator']
+__all__ = ['ProfileInterface', 'NacaProfile', 'CustomProfile',
+        'ReversePropeller', 'Blade', 'Shaft', 'Propeller', 'Deformation',
+        'ParamFile', 'RBF', 'reconstruct_f', 'scipy_bspline']
 
 from .meta import *
-from .profilebase import ProfileBase
-from .nacaprofile import NacaProfile
-from .customprofile import CustomProfile
+from .profile import ProfileInterface
+from .profile import NacaProfile
+from .profile import CustomProfile
 from .blade import Blade
 from .shaft import Shaft
 from .propeller import Propeller
 from .deform import Deformation
 from .params import ParamFile
-from .ndinterpolator import RBF, reconstruct_f, scipy_bspline 
+from .ndinterpolator import RBF, reconstruct_f, scipy_bspline
 from .reversepropeller import ReversePropeller

bladex/blade.py

@@ -479,7 +479,7 @@ def plot(self, elev=None, azim=None, ax=None, outfile=None):
         >>> blade_2.rotate(rot_angle_deg=72)
 
         >>> fig = plt.figure()
-        >>> ax = fig.gca(projection=Axes3D.name)
+        >>> ax = fig.add_subplot(projection='3d')
         >>> blade_1.plot(ax=ax)
         >>> blade_2.plot(ax=ax)
 
@@ -504,7 +504,7 @@ def plot(self, elev=None, azim=None, ax=None, outfile=None):
             ax = ax
         else:
             fig = plt.figure()
-            ax = fig.gca(projection=Axes3D.name)
+            ax = fig.add_subplot(projection='3d')
         ax.set_aspect('auto')
 
         for i in range(self.n_sections):

bladex/profile/__init__.py

@@ -0,0 +1,8 @@
+"""
+Profile init
+"""
+__all__ = ['ProfileInterface', 'NacaProfile', 'CustomProfile']
+
+from .profileinterface import ProfileInterface
+from .nacaprofile import NacaProfile
+from .customprofile import CustomProfile

bladex/nacaprofile.py → bladex/profile/nacaprofile.py

@@ -1,12 +1,12 @@
 """
-Derived module from profilebase.py to provide the airfoil coordinates for standard
-Naca profiles.
+Derived module from profilebase.py to provide the airfoil coordinates for
+standard Naca profiles.
 """
 from scipy.interpolate import splev, splrep
 import numpy as np
-from .profilebase import ProfileBase
+from .profileinterface import ProfileInterface
 
-class NacaProfile(ProfileBase):
+class NacaProfile(ProfileInterface):
     """
     Generate 4- and 5-digit NACA profiles.
 
@@ -24,29 +24,29 @@ class NacaProfile(ProfileBase):
 
         - P/10: indicates the location of the maximum camber measured from the
           leading edge. The location is normalized by the chord length.
-        
+
         - TT/100: the maximum thickness as fraction of the chord length.
 
     The profile 00TT refers to a symmetrical NACA airfoil.
 
     The NACA five-digit series describes more complex airfoil shapes.
     Its format is: LPSTT, where:
-        
+
         - L: the theoretical optimum lift coefficient at ideal
           angle-of-attack = 0.15*L
-        
+
         - P: the x-coordinate of the point of maximum camber
           (max camber at x = 0.05*P)
-        
+
         - S: indicates whether the camber is simple (S=0) or reflex (S=1)
           TT/100: the maximum thickness in percent of chord, as in a four-digit
           NACA airfoil code
 
     References:
-    
+
     - Moran, Jack (2003). An introduction to theoretical and computational
       aerodynamics. Dover. p. 7. ISBN 0-486-42879-6.
-    
+
     - Abbott, Ira (1959). Theory of Wing Sections: Including a Summary of
       Airfoil Data. New York: Dover Publications. p. 115. ISBN 978-0486605869.
 
@@ -68,7 +68,8 @@ def __init__(self, digits, n_points=240, cosine_spacing=True):
         self.n_points = n_points
         self.cosine_spacing = cosine_spacing
         self._check_args()
-        self._generate_coordinates()
+        self.generate_coordinates()
+        self.generate_parameters(convention='british')
 
     def _check_args(self):
         """
@@ -84,7 +85,10 @@ def _check_args(self):
         if self.n_points < 0:
             raise ValueError('n_points must be positive.')
 
-    def _generate_coordinates(self):
+    def generate_parameters(self, convention='british'):
+        return super().generate_parameters(convention)
+
+    def generate_coordinates(self):
         """
         Private method that generates the coordinates of the NACA 4 or 5 digits
         airfoil profile. The method assumes a zero-thickness trailing edge, and
@@ -214,4 +218,5 @@ def _generate_coordinates(self):
                     self.ydown_coordinates = yc - yt
 
         else:
-            raise Exception
+            raise Exception
+