A hotfix branch that squashes v1.0.0's packaging bug.

In addition to the packaging bug, this branch added to-dos to the README, and fixed an esoteric bug caused by incorrect interpretation of spanwise panel numbers in meshing.py.


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README.md

@@ -160,6 +160,7 @@ start, this is for you!
 * Ideally, we should fix up the style so that the entire repository has an A+ CodeFactor Rating.
 * We should fill in any of the "Properly document this..." TODO statements.
 * We should ensure that all files have between 30% and 70% comment lines.
+* We should continue to ensure that all source code is formatted using Black.
 
 ### Features
 
@@ -170,6 +171,9 @@ start, this is for you!
   Vortex-Lattice Method to Study Flapping Wings in Hover Flight." by Bruno Roccia, Sergio Preidikman, Julio Massa, and
   Dean Mook for details.
 * We should create a command-line interface or GUI.
+* We should try to implement aeroelastic effects in Ptera Software's solvers.
+* Flapping wing controls is both fascinating and complicated. We should try to create a workflow in Ptera Software for
+controls systems identification for flapping wing vehicles.
 
 ## Credits
 

pterasoftware/meshing.py

@@ -215,8 +215,8 @@ def mesh_wing(wing):
             hinge_point=inner_cross_section.control_surface_hinge_point,
         )
         outer_airfoil = outer_cross_section.airfoil.add_control_surface(
-            deflection=inner_cross_section.control_surface_deflection,
             # The inner cross section dictates control surface deflections.
+            deflection=inner_cross_section.control_surface_deflection,
             hinge_point=inner_cross_section.control_surface_hinge_point,
         )
 
@@ -297,16 +297,17 @@ def mesh_wing(wing):
             + outer_cross_section_mcl_local_up
         )
 
-        # Define number of spanwise points and panels.
-        num_spanwise_panels = wing_cross_section.num_spanwise_panels
+        # Define number of spanwise points and panels. This is based on the inner
+        # cross section.
+        num_spanwise_panels = inner_cross_section.num_spanwise_panels
         num_spanwise_coordinates = num_spanwise_panels + 1
 
-        # Get the spanwise coordinates.
-        if wing_cross_section.spanwise_spacing == "uniform":
+        # Get the spanwise coordinates. This is based on the inner cross section.
+        if inner_cross_section.spanwise_spacing == "uniform":
             nondim_spanwise_coordinates = np.linspace(
                 0, 1, num_spanwise_coordinates, endpoint=True,
             )
-        elif wing_cross_section.spanwise_spacing == "cosine":
+        elif inner_cross_section.spanwise_spacing == "cosine":
             nondim_spanwise_coordinates = ps.geometry.cosspace(
                 n_points=num_spanwise_coordinates, endpoint=True,
             )

setup.cfg

@@ -1,6 +1,6 @@
 [metadata]
 name = PteraSoftware
-version = 1.0.0
+version = 1.0.1
 author = Cameron Urban
 author_email = camerongurban@gmail.com
 description = This is an open-source, unsteady aerodynamics solver for analyzing flapping-wing flight.
@@ -39,6 +39,7 @@ keywords =
 [options]
 packages =
     pterasoftware
+    pterasoftware.airfoils
 python_requires = >= 3.7.6, < 3.8
 install_requires =
     matplotlib >= 3.2.2, < 4.0.0