diff options
Diffstat (limited to 'creator.py')
| -rw-r--r-- | creator.py | 47 |
1 files changed, 26 insertions, 21 deletions
@@ -32,7 +32,6 @@ import numpy as np from math import sin, cos, atan, sqrt import bisect as bi import matplotlib.pyplot as plt -from matplotlib.figure import Figure class Airfoil: @@ -359,29 +358,34 @@ class Stringer(Airfoil): return None -def plot_geom(airfoil): +def plot_geom(airfoil, view: False): """This function plots the airfoil's + sub-components' geometry.""" - fig = Figure() + fig, ax = plt.subplots() + ax.axis('off') + # Plot chord - x_chord = [0, airfoil.chord] - y_chord = [0, 0] - plt.plot(x_chord, y_chord, linewidth='1') + x = [0, airfoil.chord] + y = [0, 0] + fig.add_subplot(111).plot(x, y, linewidth='1') # Plot quarter chord - plt.plot(airfoil.chord / 4, 0, '.', color='g', - markersize=24, label='Quarter-chord') + fig.add_subplot(111).plot(airfoil.chord / 4, 0, + '.', color='g', markersize=24, + label='Quarter-chord') # Plot mean camber line - plt.plot(airfoil.x_c, airfoil.z_c, '-.', color='r', linewidth='2', - label='Mean camber line') + fig.add_subplot(111).plot(airfoil.x_c, airfoil.z_c, + '-.', color='r', linewidth='2', + label='Mean camber line') # Plot airfoil surfaces - plt.fill(airfoil.x, airfoil.z, color='b', linewidth='1', fill=False) + fig.add_subplot(111).plot(airfoil.x, airfoil.z, + color='b', linewidth='1') # Plot spars try: for _ in range(len(airfoil.spar.x)): x = (airfoil.spar.x[_]) y = (airfoil.spar.z[_]) - plt.plot(x, y, '-', color='y', linewidth='4') + fig.add_subplot(111).plot(x, y, '-', color='y', linewidth='4') except AttributeError: print('No spars to plot.') # Plot stringers @@ -389,21 +393,22 @@ def plot_geom(airfoil): for _ in range(0, len(airfoil.stringer.x)): x = airfoil.stringer.x[_] y = airfoil.stringer.z[_] - plt.plot(x, y, '.', color='y', markersize=12) + fig.add_subplot(111).plot(x, y, '.', color='y', markersize=12) except AttributeError: print('No stringers to plot.') # Graph formatting - plt.xlabel('X axis') - plt.ylabel('Z axis') - plot_bound = max(airfoil.x) - plt.xlim(- 0.10 * plot_bound, 1.10 * plot_bound) - plt.ylim(- (1.10 * plot_bound / 2), (1.10 * plot_bound / 2)) + ax.set(title='NACA ' + str(airfoil.naca_num) + ' airfoil', + xlabel='X axis', + ylabel='Z axis') + plt.grid(axis='both', linestyle=':', linewidth=1) plt.gca().set_aspect('equal', adjustable='box') plt.gca().legend() - plt.grid(axis='both', linestyle=':', linewidth=1) - plt.show() - return None + if view == True: + plt.show() + else: + pass + return fig, ax def main(): |