various inconsistency fix

3 files changed, 18 insertions, 20 deletions

diff --git a/creator.py b/creator.py
index 366909b..1e375a6 100644
--- a/creator.py
+++ b/creator.py
@@ -91,13 +91,13 @@ class Coordinates:
         print('z_l the lower z-coordinates:\n', np.around(self.z_l, round))
         return None
 
-    def info_save(self, save_dir_path, number):
+    def info_save(self, save_path, number):
         '''
         Save all the object's coordinates (must be full path).
         '''
 
         file_name = '{}_{}.txt'.format(str(self).lower(), number)
-        full_path = os.path.join(save_dir_path, file_name)
+        full_path = os.path.join(save_path, file_name)
         try:
             with open(full_path, 'w') as sys.stdout:
                 self.info_print(6)
diff --git a/evaluator.py b/evaluator.py
index f6d0afc..b0d90fd 100644
--- a/evaluator.py
+++ b/evaluator.py
@@ -60,7 +60,7 @@ class Airfoil:
         This function's output is piped to the 'save_data' function below.
         '''
 
-        name = '    CREATOR DATA    '
+        name = '    EVALUATOR DATA    '
         num_of_dashes = len(name)
 
         print(num_of_dashes * '-')
@@ -142,13 +142,13 @@ class Airfoil:
             (len(x_stringers) * area)
         return(x_centroid, z_centroid)
 
-    def get_I_x():
+    def get_I_x(self):
         pass
 
-    def get_I_z():
+    def get_I_z(self):
         pass
 
-    def get_I_xz():
+    def get_I_xz(self):
         pass
 
     def analysis(self):
@@ -216,6 +216,4 @@ class Airfoil:
         plt.gca().set_aspect('equal', adjustable='box')
         plt.grid(axis='both', linestyle=':', linewidth=1)
         plt.show()
-        # plt.pause(1)
-        # plt.close()
         return None
diff --git a/main.py b/main.py
index e771092..a112542 100644
--- a/main.py
+++ b/main.py
@@ -23,8 +23,8 @@ start_time = time.time()
 
 # Airfoil dimensions
 NACA_NUM = 2412
-CHORD_LENGTH = 20
-SEMI_SPAN = 20
+CHORD_LENGTH = 40
+SEMI_SPAN = 50
 
 # Component masses
 AIRFOIL_MASS = 10  # lbs
@@ -33,7 +33,7 @@ STRINGER_MASS = 5  # lbs
 
 # Area
 STRINGER_AREA = 0.1  # sqin
-TOP_STRINGERS = 4
+TOP_STRINGERS = 8
 BOTTOM_STRINGERS = 6
 NOSE_TOP_STRINGERS = 4
 NOSE_BOTTOM_STRINGERS = 7
@@ -62,8 +62,8 @@ def main():
         # Define NACA airfoil coordinates and mass
         af.add_naca(NACA_NUM)
         af.add_mass(AIRFOIL_MASS)
-        # af.info_print(2)
-        # af.info_save(SAVE_PATH, _)
+        af.info_print(2)
+        af.info_save(SAVE_PATH, _)
 
         # Create spar instance
         af.spar = creator.Spar()
@@ -71,8 +71,8 @@ def main():
         af.spar.add_coord(af.coord, 0.15)
         af.spar.add_coord(af.coord, 0.55)
         af.spar.add_mass(SPAR_MASS)
-        # af.spar.info_print(2)
-        # af.spar.info_save(SAVE_PATH, _)
+        af.spar.info_print(2)
+        af.spar.info_save(SAVE_PATH, _)
 
         # Create stringer instance
         af.stringer = creator.Stringer()
@@ -84,19 +84,19 @@ def main():
                               BOTTOM_STRINGERS)
         af.stringer.add_area(STRINGER_AREA)
         af.stringer.add_mass(STRINGER_MASS)
-        # af.stringer.info_print(2)
-        # af.stringer.info_save(SAVE_PATH, _)
+        af.stringer.info_print(2)
+        af.stringer.info_save(SAVE_PATH, _)
 
         # Plot components with matplotlib
-        # af.plot()
+        af.plot()
 
         # evaluator.Evaluator instance contains airfoil analysis results.
         eval = evaluator.Airfoil(af)
         # The analysis is performed in the evaluator.py module.
         eval.analysis()
         eval.info_print(2)
-        # eval.info_save(SAVE_PATH, _)
-        # eval.plot()
+        eval.info_save(SAVE_PATH, _)
+        eval.plot()
 
     # Print final execution time
     print("--- %s seconds ---" % (time.time() - start_time))