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-rw-r--r--creator.py85
-rw-r--r--main.py68
2 files changed, 82 insertions, 71 deletions
diff --git a/creator.py b/creator.py
index d75661f..601e849 100644
--- a/creator.py
+++ b/creator.py
@@ -186,8 +186,16 @@ class Airfoil(Coordinates):
# Densify x-coordinates 10 times for first 1/4 chord length
x_chord_25_percent = round(self.chord / 4)
- x_chord = [x / 10 for x in range(x_chord_25_percent * 10)]
- x_chord.extend([x for x in range(x_chord_25_percent, self.chord + 1)])
+
+ x_chord = [i / 10 for i in range(x_chord_25_percent * 10)]
+ x_chord.extend(i for i in range(x_chord_25_percent, self.chord + 1))
+ # Reversed list for our lower airfoil coordinate densification
+ x_chord_rev = [i for i in range(
+ self.chord, x_chord_25_percent, -1)]
+ ext = [i / 10 for i in range(x_chord_25_percent * 10, -1, -1)]
+ x_chord_rev.extend(ext)
+ print(len(x_chord))
+ print(len(x_chord_rev))
# Generate our airfoil geometry from previous sub-functions.
for x in x_chord:
@@ -195,9 +203,7 @@ class Airfoil(Coordinates):
self.y_c.append(get_camber(x))
self.x.append(get_upper_coord(x)[0])
self.z.append(get_upper_coord(x)[1])
- # Behold the true power of Python list slicing!
- # (This special list index reverses the list.)
- for x in x_chord[::-1]:
+ for x in x_chord_rev:
self.x.append(get_lower_coord(x)[0])
self.z.append(get_lower_coord(x)[1])
return None
@@ -232,7 +238,6 @@ class Spar(Coordinates):
None
'''
# Airfoil surface coordinates
- # unpacked from 'coordinates' (list of lists in 'Coordinates').
x = airfoil.x
z = airfoil.z
# Scaled spar location with regards to chord
@@ -242,13 +247,21 @@ class Spar(Coordinates):
# bisect_right: returns index of first value in x > loc
# starting from [-1] (last list element).
# This ensures that the spar geom intersects with airfoil geom.
- spar_x = bi.bisect_left(x, loc) # index of spar's x
- spar_x = bi.bisect_left(x, loc) # index of spar's x
+ spar_x_u = bi.bisect_left(x, loc) # index of spar's x_u
+ spar_z_u = bi.bisect_left(z, loc)
+ spar_x_l = bi.bisect_left(x[::-1], loc) # index of spar's x_l
+ spar_z_l = bi.bisect_left(z[::-1], loc)
+ print(len(x))
+ print(len(z))
# These x and y coordinates are assigned to the spar, NOT airfoil.
- self.x.append(x[spar_x])
- self.z.append(z[spar_x])
- self.x.append(x[spar_x])
- self.z.append(z[spar_x])
+ # print(spar_x_u)
+ # print(spar_z_u)
+ # print(spar_x_l)
+ # print(spar_z_l)
+ # self.x.append(x[spar_x_u])
+ # self.z.append(z[spar_z_u])
+ # self.x.append(x[spar_x_l])
+ # self.z.append(z[spar_z_l])
return None
def add_spar_caps(self, spar_cap_area):
@@ -354,40 +367,38 @@ def plot_geom(airfoil):
plt.plot(airfoil.chord / 4, 0, '.', color='g',
markersize=24, label='Quarter-chord')
# 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, airfoil.z,
- '', color='b', linewidth='1')
- # Plot lower surface
- plt.plot(airfoil.x, airfoil.z,
- '', color='b', linewidth='1')
+ # Plot airfoil surfaces
+ plt.fill(airfoil.x, airfoil.z, '', color='b', linewidth='1', fill=False)
# Plot spars
- for _ in range(0, len(airfoil.spar.x)):
- x = (airfoil.spar.x[_], airfoil.spar.x[_])
- y = (airfoil.spar.z[_], airfoil.spar.z[_])
- plt.plot(x, y, '.-', color='b')
-
+ try:
+ for _ in range(0, len(airfoil.spar.x)):
+ x = (airfoil.spar.x[_], airfoil.spar.x[_])
+ y = (airfoil.spar.z[_], airfoil.spar.z[_])
+ plt.plot(x, y, '.-', color='b')
+ except AttributeError:
+ print('No spars to plot.')
# Plot upper stringers
- for _ in range(0, len(airfoil.stringer.x)):
- x = airfoil.stringer.x[_]
- y = airfoil.stringer.z[_]
- plt.plot(x, y, '.', color='y', markersize=12)
- # Plot lower stringers
- for _ in range(0, len(airfoil.stringer.x)):
- x = airfoil.stringer.x[_]
- y = airfoil.stringer.z[_]
- plt.plot(x, y, '.', color='y', markersize=12)
+ try:
+ for _ in range(0, len(airfoil.stringer.x)):
+ x = airfoil.stringer.x[_]
+ y = airfoil.stringer.z[_]
+ plt.plot(x, y, '.', color='y', markersize=12)
+ except AttributeError:
+ print('No stringers to plot.')
+ # # Plot lower stringers
+ # for _ in range(0, len(airfoil.stringer.x)):
+ # x = airfoil.stringer.x[_]
+ # y = airfoil.stringer.z[_]
+ # plt.plot(x, y, '.', color='y', markersize=12)
# Graph formatting
plt.xlabel('X axis')
plt.ylabel('Z axis')
- plot_bound = airfoil.x[-1]
- plt.xlim(- 0.10 * plot_bound, 1.10 * plot_bound)
- plt.ylim(- (1.10 * plot_bound / 2), (1.10 * plot_bound / 2))
+ # plot_bound = airfoil.x[-1]
plt.gca().set_aspect('equal', adjustable='box')
plt.gca().legend()
plt.grid(axis='both', linestyle=':', linewidth=1)
diff --git a/main.py b/main.py
index fd8855f..09d33e6 100644
--- a/main.py
+++ b/main.py
@@ -24,8 +24,8 @@ start_time = time.time()
# Airfoil dimensions
NACA_NUM = 2412
-CHORD_LENGTH = 40
-SEMI_SPAN = 50
+CHORD_LENGTH = 12
+SEMI_SPAN = 20
# Airfoil thickness
T_UPPER = 0.1
@@ -41,9 +41,9 @@ SPAR_CAP_AREA = 0.3 # sqin
STRINGER_AREA = 0.1 # sqin
# Amount of stringers
-TOP_STRINGERS = 0
+TOP_STRINGERS = 2
BOTTOM_STRINGERS = 18
-NOSE_TOP_STRINGERS = 0
+NOSE_TOP_STRINGERS = 5
NOSE_BOTTOM_STRINGERS = 5
# population information & save path
@@ -71,42 +71,42 @@ def main():
af.add_naca(NACA_NUM)
af.add_mass(AIRFOIL_MASS)
# af.info_print(2)
- # af.info_save(SAVE_PATH, _)
-
- # Create spar instance
- af.spar = creator.Spar()
- # Define the spar coordinates and mass, stored in single spar object
- af.spar.add_coord(af, 0.15)
- af.spar.add_coord(af, 0.55)
- # Automatically adds spar caps for all spars previously defined
- af.spar.add_spar_caps(SPAR_CAP_AREA)
- af.spar.add_mass(SPAR_MASS)
- # af.spar.info_print(2)
- # af.spar.info_save(SAVE_PATH, _)
-
- # Create stringer instance
- af.stringer = creator.Stringer()
- # Compute the stringer coordinates from their quantity in each zone
- af.stringer.add_coord(af,
- NOSE_TOP_STRINGERS,
- TOP_STRINGERS,
- NOSE_BOTTOM_STRINGERS,
- 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.info_save(SAVE_PATH, _)
+
+ # # Create spar instance
+ # af.spar = creator.Spar()
+ # # Define the spar coordinates and mass, stored in single spar object
+ # af.spar.add_coord(af, 0.15)
+ # af.spar.add_coord(af, 0.55)
+ # # Automatically adds spar caps for all spars previously defined
+ # af.spar.add_spar_caps(SPAR_CAP_AREA)
+ # af.spar.add_mass(SPAR_MASS)
+ # # af.spar.info_print(2)
+ # # af.spar.info_save(SAVE_PATH, _)
+ #
+ # # Create stringer instance
+ # af.stringer = creator.Stringer()
+ # # Compute the stringer coordinates from their quantity in each zone
+ # af.stringer.add_coord(af,
+ # NOSE_TOP_STRINGERS,
+ # TOP_STRINGERS,
+ # NOSE_BOTTOM_STRINGERS,
+ # 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, _)
# Plot components with matplotlib
- # creator.plot_geom(af)
+ creator.plot_geom(af)
# Evaluator object contains airfoil analysis results.
- eval = evaluator.Evaluator(af)
+ # eval = evaluator.Evaluator(af)
# The analysis is performed in the evaluator.py module.
- eval.analysis()
+ # eval.analysis()
# eval.info_print(2)
- eval.info_save(SAVE_PATH, _)
- evaluator.plot_geom(eval)
+ # eval.info_save(SAVE_PATH, _)
+ # evaluator.plot_geom(eval)
# evaluator.plot_lift(eval)
# Print final execution time
Copyright 2019--2024 Marius PETER