diff options
Diffstat (limited to 'creator.py')
| -rw-r--r-- | creator.py | 16 |
1 files changed, 11 insertions, 5 deletions
@@ -81,9 +81,9 @@ class Coordinates: print('Mass:', self.mass) print('============================') print('x_u the upper x-coordinates:\n', np.around(self.x_u, round)) - print('z_u the upper y-coordinates:\n', np.around(self.z_u, round)) + print('z_u the upper z-coordinates:\n', np.around(self.z_u, round)) print('x_l the lower x-coordinates:\n', np.around(self.x_l, round)) - print('z_l the lower y-coordinates:\n', np.around(self.z_l, round)) + print('z_l the lower z-coordinates:\n', np.around(self.z_l, round)) return None def save_info(self, save_dir_path, number): @@ -123,8 +123,8 @@ class Airfoil(Coordinates): # NACA number self.naca_num = int() # Mean camber line - self.x_c = [] # Contains only integers from 0 to self.chord - self.y_c = [] # Contains floats + self.x_c = [] + self.y_c = [] def add_naca(self, naca_num): """ @@ -167,7 +167,7 @@ class Airfoil(Coordinates): Returns thickness from 1 'x' along the airfoil chord. """ y_t = 5 * t * self.chord * ( - +0.2969 * sqrt(x / 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 @@ -213,6 +213,12 @@ class Airfoil(Coordinates): def add_mass(self, mass): self.mass = mass + def print_info(self, round): + super().print_info(round) + print('x_c the camber x-coordinates:\n', np.around(self.x_u, round)) + print('z_c the camber z-coordinates:\n', np.around(self.x_u, round)) + return None + class Spar(Coordinates): """Contains a single spar's location.""" |