From ee69827c8efa1b563897e37a5ed220c7fadbb2e3 Mon Sep 17 00:00:00 2001
From: Marius Peter <blendoit@gmail.com>
Date: Thu, 6 Jun 2019 16:52:39 -0700
Subject: Testing the integration between Atom editor and GitHub.

---
 __init__.py                        |   4 +++-
 __pycache__/creator.cpython-37.pyc | Bin 0 -> 9785 bytes
 creator.py                         |  40 ++++++++++++++++++++-----------------
 3 files changed, 25 insertions(+), 19 deletions(-)
 create mode 100644 __pycache__/creator.cpython-37.pyc

diff --git a/__init__.py b/__init__.py
index a7e70a3..3e60a6f 100644
--- a/__init__.py
+++ b/__init__.py
@@ -5,7 +5,7 @@
 # the Free Software Foundation, either version 3 of the License, or
 # (at your option) any later version.
 #
-# This program is distributed in the hope that it will be useful,
+# This program is distribguted in the hope that it will be useful,
 # but WITHOUT ANY WARRANTY; without even the implied warranty of
 # MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
 # GNU General Public License for more details.
@@ -15,3 +15,5 @@
 __author__ = "Marius Peter"
 __version__ = "2.1"
 __revision__ = "2.1.1"
+
+# Foobie foobar
diff --git a/__pycache__/creator.cpython-37.pyc b/__pycache__/creator.cpython-37.pyc
new file mode 100644
index 0000000..9933593
Binary files /dev/null and b/__pycache__/creator.cpython-37.pyc differ
diff --git a/creator.py b/creator.py
index 59c8436..f826a14 100644
--- a/creator.py
+++ b/creator.py
@@ -22,7 +22,7 @@ import matplotlib.pyplot as plt
 import matplotlib as mpl
 from mpl_toolkits.mplot3d import Axes3D
 
-
+# hello im just dicking around
 # This variable is required for main.py constant wing dimensions
 # to be passed to inheriting classes (Airfoil, Spar, Stringer, Rib).
 # This way, we don't have to redeclare our coordinates as parameters for
@@ -117,13 +117,12 @@ class Airfoil(Coordinates):
             x_c = x
             y_c = float()
             if 0 <= x < p_c:
-                y_c = (m / (p ** 2)) * (2 * p
-                                        * (x / self.chord)
-                                        - (x / self.chord) ** 2)
+                y_c = (m / (p**2)) * (2 * p * (x / self.chord) -
+                                      (x / self.chord)**2)
             elif p_c <= x <= self.chord:
-                y_c = (m / ((1 - p) ** 2)) * ((1 - 2 * p)
-                                              + 2 * p * (x / self.chord)
-                                              - (x / self.chord) ** 2)
+                y_c = (m /
+                       ((1 - p)**2)) * ((1 - 2 * p) + 2 * p *
+                                        (x / self.chord) - (x / self.chord)**2)
             else:
                 print('x-coordinate for camber is out of bounds. '
                       'Check that 0 < x <= chord.')
@@ -135,11 +134,12 @@ class Airfoil(Coordinates):
             """
             y_t = float()
             if 0 <= x <= self.chord:
-                y_t = 5 * t * self.chord * (0.2969 * sqrt(x / self.chord)
-                                            - 0.1260 * (x / self.chord)
-                                            - 0.3516 * (x / self.chord) ** 2
-                                            + 0.2843 * (x / self.chord) ** 3
-                                            - 0.1015 * (x / self.chord) ** 4)
+                y_t = 5 * t * self.chord * (0.2969 * sqrt(x / self.chord) -
+                                            0.1260 *
+                                            (x / self.chord) - 0.3516 *
+                                            (x / self.chord)**2 + 0.2843 *
+                                            (x / self.chord)**3 - 0.1015 *
+                                            (x / self.chord)**4)
             else:
                 print('x-coordinate for thickness is out of bounds. '
                       'Check that 0 < x <= chord.')
@@ -151,9 +151,9 @@ class Airfoil(Coordinates):
             """
             dy_c = float()
             if 0 <= x < p_c:
-                dy_c = ((2 * m)/p ** 2) * (p - x / self.chord)
+                dy_c = ((2 * m) / p**2) * (p - x / self.chord)
             elif p_c <= x <= self.chord:
-                dy_c = (2 * m) / ((1 - p) ** 2) * (p - x / self.chord)
+                dy_c = (2 * m) / ((1 - p)**2) * (p - x / self.chord)
             return dy_c
 
         def get_theta(dy_c):
@@ -169,7 +169,7 @@ class Airfoil(Coordinates):
             elif x == self.chord:
                 x_u = x - self.y_t[x] * sin(self.theta[x])
                 y_u = 0  # Make upper curve finish at y = 0
-            return(x_u, y_u)
+            return (x_u, y_u)
 
         def get_lower_coordinates(x):
             x_l = float()
@@ -180,7 +180,7 @@ class Airfoil(Coordinates):
             elif x == self.chord:
                 x_l = (x + self.y_t[x] * sin(self.theta[x]))
                 y_l = 0  # Make lower curve finish at y = 0
-            return(x_l, y_l)
+            return (x_l, y_l)
 
         # Generate all our wing geometries from previous sub-functions
         for x in range(0, self.chord + 1):
@@ -233,7 +233,7 @@ class Airfoil(Coordinates):
         Save all the declared geometry to save_dir_path (must be full path).
         """
         file_name = 'airfoil_%s' % airfoil_number
-        full_path = os.path.join(save_dir_path, file_name+'.txt')
+        full_path = os.path.join(save_dir_path, file_name + '.txt')
         file = open(full_path, 'w')
         sys.stdout = file
         self.print_geometry(4)
@@ -341,7 +341,11 @@ def plot(airfoil, spar):
     y_chord = [0, 0]
     plt.plot(x_chord, y_chord, linewidth='1')
     # Plot mean camber line
-    plt.plot(airfoil.x_c, airfoil.y_c, '-.', color='r', linewidth='2',
+    plt.plot(airfoil.x_c,
+             airfoil.y_c,
+             '-.',
+             color='r',
+             linewidth='2',
              label='mean camber line')
     # Plot upper surface
     plt.plot(airfoil.x_u, airfoil.y_u, '', color='b', linewidth='1')
-- 
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