diff options
| -rw-r--r-- | creator.py | 63 |
1 files changed, 32 insertions, 31 deletions
@@ -45,9 +45,7 @@ class Coordinates: def __init__(self, chord, semi_span): # Global dimensions - self.chord = chord - if chord < 10: - self.chord = 10 + self.chord = chord if chord > 10 else 10 self.semi_span = semi_span # mass and area self.mass = float() @@ -164,12 +162,12 @@ class Airfoil(Coordinates): x_c = x y_c = float() if 0 <= x < p_c: - y_c = (m / (p**2)) * (2 * p * (x / self.chord) - - (x / self.chord)**2) + y_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) + 2 * p * - (x / self.chord) - (x / self.chord)**2) + y_c = (m / ((1 - p)**2)) * ((1 - 2 * p) + + 2 * p * (x / self.chord) + - (x / self.chord)**2) else: print('x-coordinate for camber is out of bounds. ' 'Check that 0 < x <= chord.') @@ -181,29 +179,23 @@ class Airfoil(Coordinates): """ y_t = float() if 0 <= x <= self.chord: - y_t = 5 * t * self.chord * (0.2969 * sqrt(x / self.chord) - - 0.1260 * - (x / self.chord) - 0.3516 * - (x / self.chord)**2 + 0.2843 * - (x / self.chord)**3 - 0.1015 * - (x / self.chord)**4) + y_t = 5 * t * self.chord * ( + +0.2969 * sqrt(x / self.chord) + - 0.1260 * (x / self.chord) + - 0.3516 * (x / self.chord)**2 + + 0.2843 * (x / self.chord)**3 + - 0.1015 * (x / self.chord)**4) else: print('x-coordinate for thickness is out of bounds. ' 'Check that 0 < x <= chord.') return y_t - def get_dy_c(x): - """ - Returns dy_c/dx from 1 'x' along the airfoil chord. - """ + def get_theta(x): dy_c = float() if 0 <= x < p_c: dy_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) - return dy_c - - def get_theta(dy_c): theta = atan(dy_c) return theta @@ -211,10 +203,11 @@ class Airfoil(Coordinates): x_u = float() z_u = float() if 0 <= x < self.chord: - x_u = x - self.y_t[x] * sin(self.theta[x]) - z_u = self.y_c[x] + self.y_t[x] * cos(self.theta[x]) + x_u = x - get_thickness(x) * sin(get_theta(x)) + z_u = get_camber(x)[1] + get_thickness(x) * \ + cos(get_theta(x)) elif x == self.chord: - x_u = x - self.y_t[x] * sin(self.theta[x]) + x_u = x - get_thickness(x) * sin(get_theta(x)) z_u = 0 # Make upper curve finish at y = 0 return (x_u, z_u) @@ -222,20 +215,28 @@ class Airfoil(Coordinates): x_l = float() z_l = float() if 0 <= x < self.chord: - x_l = (x + self.y_t[x] * sin(self.theta[x])) - z_l = (self.y_c[x] - self.y_t[x] * cos(self.theta[x])) + x_l = (x + get_thickness(x) * sin(get_theta(x))) + z_l = (get_camber(x)[1] - get_thickness(x) + * cos(get_theta(x))) elif x == self.chord: - x_l = (x + self.y_t[x] * sin(self.theta[x])) + x_l = (x + get_thickness(x) * sin(get_theta(x))) z_l = 0 # Make lower curve finish at y = 0 return (x_l, z_l) - # Generate all our wing geometries from previous sub-functions - for x in range(0, self.chord + 1): + # Generate our airfoil geometry from previous sub-functions. + # Geometry is densest at leading edge: airfoil slope is highest here. + x_chord_10_percent = round(self.chord / 10) + # Densify x-coordinates 10 times for first 10% of the chord length + x_chord = [x / 10 for x in range(x_chord_10_percent * 10)] + x_chord.extend([x for x in range(x_chord_10_percent, self.chord + 1)]) + print(x_chord) + + for x in x_chord: self.x_c.append(get_camber(x)[0]) self.y_c.append(get_camber(x)[1]) self.y_t.append(get_thickness(x)) - self.dy_c.append(get_dy_c(x)) - self.theta.append(get_theta(self.dy_c[x])) + self.dy_c.append(x) + self.theta.append(get_theta(x)) self.x_u.append(get_upper_coordinates(x)[0]) self.z_u.append(get_upper_coordinates(x)[1]) self.x_l.append(get_lower_coordinates(x)[0]) |