diff options
Diffstat (limited to 'creator.py')
| -rw-r--r-- | creator.py | 37 |
1 files changed, 16 insertions, 21 deletions
@@ -122,7 +122,7 @@ class Airfoil(Coordinates): self.naca_num = int() # Mean camber line self.x_c = [] - self.y_c = [] + self.z_c = [] def add_naca(self, naca_num): ''' @@ -148,22 +148,22 @@ class Airfoil(Coordinates): def get_camber(x): ''' - Returns camber y-coordinate from 1 'x' along the airfoil chord. + Returns camber z-coordinate from 1 'x' along the airfoil chord. ''' - y_c = float() + z_c = float() if 0 <= x < p_c: - y_c = (m / (p ** 2)) * (2 * p * (x / self.chord) + z_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) + z_c = (m / ((1 - p) ** 2)) * ((1 - 2 * p) + 2 * p * (x / self.chord) - (x / self.chord) ** 2) - return (y_c * self.chord) + return (z_c * self.chord) def get_thickness(x): - ''' - Returns thickness from 1 'x' along the airfoil chord. - ''' + '''Returns thickness from 1 'x' along the airfoil chord.''' + + x = 0 if x < 0 else x y_t = 5 * t * self.chord * ( + 0.2969 * sqrt(x / self.chord) - 0.1260 * (x / self.chord) @@ -173,12 +173,12 @@ class Airfoil(Coordinates): return y_t def get_theta(x): - dy_c = float() + dz_c = float() if 0 <= x < p_c: - dy_c = ((2 * m) / p ** 2) * (p - x / self.chord) + dz_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) - theta = atan(dy_c) + dz_c = (2 * m) / ((1 - p) ** 2) * (p - x / self.chord) + theta = atan(dz_c) return theta def get_upper_coord(x): @@ -204,7 +204,7 @@ class Airfoil(Coordinates): # Generate our airfoil geometry from previous sub-functions. for x in x_chord: self.x_c.append(x) - self.y_c.append(get_camber(x)) + self.z_c.append(get_camber(x)) self.x.append(get_upper_coord(x)[0]) self.z.append(get_upper_coord(x)[1]) for x in x_chord_rev: @@ -361,7 +361,7 @@ 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.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) @@ -374,7 +374,7 @@ def plot_geom(airfoil): plt.plot(x, y, '-', color='b') except AttributeError: print('No spars to plot.') - # Plot upper stringers + # Plot stringers try: for _ in range(0, len(airfoil.stringer.x)): x = airfoil.stringer.x[_] @@ -382,11 +382,6 @@ def plot_geom(airfoil): 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') |