From 4ee52cf24db8148c54f02022517a06b662509f92 Mon Sep 17 00:00:00 2001
From: Marius Peter <blendoit@gmail.com>
Date: Thu, 20 Jun 2019 18:02:31 -0700
Subject: elliptical and rectangular lift distributions

---
 creator.py   | 20 ++++++++++----------
 evaluator.py | 26 ++++++++++++++++++--------
 main.py      |  2 ++
 3 files changed, 30 insertions(+), 18 deletions(-)

diff --git a/creator.py b/creator.py
index 5c01d9c..1f02e71 100644
--- a/creator.py
+++ b/creator.py
@@ -154,12 +154,12 @@ class Airfoil(Coordinates):
             """
             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)
             return (y_c * self.chord)
 
         def get_thickness(x):
@@ -169,17 +169,17 @@ class Airfoil(Coordinates):
             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)
+                - 0.3516 * (x / self.chord) ** 2
+                + 0.2843 * (x / self.chord) ** 3
+                - 0.1015 * (x / self.chord) ** 4)
             return y_t
 
         def get_theta(x):
             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)
             theta = atan(dy_c)
             return theta
 
diff --git a/evaluator.py b/evaluator.py
index 824b578..f4768e1 100644
--- a/evaluator.py
+++ b/evaluator.py
@@ -13,7 +13,24 @@
 # You should have received a copy of the GNU General Public License
 # along with this program.  If not, see <https://www.gnu.org/licenses/>.
 
-# F_z =
+from math import sin, cos, atan, sqrt
+
+
+def get_total_mass(*component):
+    total_mass = float()
+    for _ in component:
+        total_mass += _.mass
+    return total_mass
+
+
+def lift_rectangular(lift, semi_span):
+    L_prime = lift / (semi_span * 2)
+    return L_prime
+
+
+def lift_elliptical(L_0, y, semi_span):
+    L_prime = L_0 * sqrt(1 - (y / semi_span) ** 2)
+    return L_prime
 
 
 def get_centroid(airfoil):
@@ -25,10 +42,3 @@ def get_centroid(airfoil):
         numerator += _ * area
     # denominator
     # z_c =
-
-
-def get_total_mass(self, *component):
-    total_mass = float()
-    for _ in component:
-        total_mass += _.mass
-    return total_mass
diff --git a/main.py b/main.py
index ad24bb2..0631bc9 100644
--- a/main.py
+++ b/main.py
@@ -76,6 +76,8 @@ def main():
         af.stringer.add_mass(STRINGER_MASS)
         # af.stringer.print_info(2)
 
+        print(evaluator.get_total_mass(af, af.spar, af.stringer))
+
         # Plot components with matplotlib
         creator.plot(af, af.spar, af.stringer)
 
-- 
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