diff options
Diffstat (limited to 'creator.py')
| -rw-r--r-- | creator.py | 85 |
1 files changed, 48 insertions, 37 deletions
@@ -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) |