diff options
Diffstat (limited to 'creator.py')
| -rw-r--r-- | creator.py | 51 |
1 files changed, 26 insertions, 25 deletions
@@ -13,6 +13,7 @@ # You should have received a copy of the GNU General Public License # along with this program. If not, see <https://www.gnu.org/licenses/>. + import sys import os.path import numpy as np @@ -29,7 +30,7 @@ global parent class Coordinates: - """ + ''' All airfoil components need the following: Parameters: @@ -41,7 +42,7 @@ class Coordinates: * Save component coordinates to file specified in main.py So, all component classes inherit from class Coordinates. - """ + ''' def __init__(self, chord, semi_span): # Global dimensions @@ -69,18 +70,18 @@ class Coordinates: return type(self).__name__ def print_info(self, round): - """ + ''' Print all the component's coordinates to the terminal. This function's output is piped to the 'save_coord' function below. - """ - print('============================') - print(' CREATOR DATA ') + ''' + print(20 * '-') + print(' CREATOR DATA ') print('Component:', str(self)) print('Chord length:', self.chord) print('Semi-span:', self.semi_span) print('Mass:', self.mass) - print('============================') + print(20 * '-') print('x_u the upper x-coordinates:\n', np.around(self.x_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)) @@ -88,15 +89,15 @@ class Coordinates: return None def save_info(self, save_dir_path, number): - """ + ''' Save all the object's coordinates (must be full path). - """ + ''' - file_name = '{}_{}.txt'.format(self, number) + file_name = '{}_{}.txt'.format(str(self).lower(), number) full_path = os.path.join(save_dir_path, file_name) try: with open(full_path, 'w') as sys.stdout: - self.print_info(2) + self.print_info(6) # This line required to reset behavior of sys.stdout sys.stdout = sys.__stdout__ print('Successfully wrote to file {}'.format(full_path)) @@ -115,7 +116,7 @@ class Coordinates: class Airfoil(Coordinates): - """This class enables the creation of a single NACA airfoil.""" + '''This class enables the creation of a single NACA airfoil.''' def __init__(self): global parent @@ -128,7 +129,7 @@ class Airfoil(Coordinates): self.y_c = [] def add_naca(self, naca_num): - """ + ''' This function generates geometry for our chosen NACA airfoil shape. The nested functions perform the required steps to generate geometry, and can be called to solve the geometry y-coordinate for any 'x' input. @@ -139,7 +140,7 @@ class Airfoil(Coordinates): Return: None - """ + ''' # Variables extracted from 'naca_num' argument passed to the function self.naca_num = naca_num @@ -150,9 +151,9 @@ class Airfoil(Coordinates): p_c = p * self.chord def get_camber(x): - """ + ''' Returns camber y-coordinate from 1 'x' along the airfoil chord. - """ + ''' y_c = float() if 0 <= x < p_c: y_c = (m / (p ** 2)) * (2 * p * (x / self.chord) @@ -164,9 +165,9 @@ class Airfoil(Coordinates): return (y_c * self.chord) def get_thickness(x): - """ + ''' Returns thickness from 1 'x' along the airfoil chord. - """ + ''' y_t = 5 * t * self.chord * ( + 0.2969 * sqrt(x / self.chord) - 0.1260 * (x / self.chord) @@ -222,14 +223,14 @@ class Airfoil(Coordinates): class Spar(Coordinates): - """Contains a single spar's location.""" + '''Contains a single spar's location.''' global parent def __init__(self): super().__init__(parent.chord, parent.semi_span) def add_coord(self, airfoil_coord, spar_x): - """ + ''' Add a single spar at the % chord location given to function. Parameters: @@ -239,7 +240,7 @@ class Spar(Coordinates): Return: None - """ + ''' # Airfoil surface coordinates # unpacked from 'coordinates' (list of lists in 'Coordinates'). x_u = airfoil_coord[0] @@ -266,7 +267,7 @@ class Spar(Coordinates): class Stringer(Coordinates): - """Contains the coordinates of all stringers.""" + '''Contains the coordinates of all stringers.''' global parent def __init__(self): @@ -275,7 +276,7 @@ class Stringer(Coordinates): def add_coord(self, airfoil_coord, spar_coord, stringer_u_1, stringer_u_2, stringer_l_1, stringer_l_2): - """ + ''' Add equally distributed stringers to four airfoil locations (upper nose, lower nose, upper surface, lower surface). @@ -289,7 +290,7 @@ class Stringer(Coordinates): Returns: None - """ + ''' # Airfoil surface coordinates # unpacked from 'coordinates' (list of lists in 'Coordinates'). @@ -359,7 +360,7 @@ class Stringer(Coordinates): def plot(airfoil, spar, stringer): - """This function plots the elements passed as arguments.""" + '''This function plots the elements passed as arguments.''' # Plot chord x_chord = [0, airfoil.chord] |