diff options
Diffstat (limited to 'tools')
| -rw-r--r-- | tools/creator.py | 72 |
1 files changed, 37 insertions, 35 deletions
diff --git a/tools/creator.py b/tools/creator.py index 6d074f8..d345a00 100644 --- a/tools/creator.py +++ b/tools/creator.py @@ -12,7 +12,6 @@ # # You should have received a copy of the GNU General Public License # along with this program. If not, see <https://www.gnu.org/licenses/>. - """ The creator.py module contains class definitions for coordinates and various components we add to an airfoil (spars, stringers, and ribs). @@ -57,7 +56,7 @@ class Airfoil: self.area = float() # Component material self.material = str() - # Coordinates + # Coordinate self.x = [] self.z = [] @@ -102,31 +101,32 @@ class Airfoil: """ z_c = float() if 0 <= x < p_c: - z_c = (m / (p ** 2)) * (2 * p * (x / self.chord) - - (x / self.chord) ** 2) + z_c = (m / (p**2)) * (2 * p * (x / self.chord) - + (x / self.chord)**2) elif p_c <= x <= self.chord: - z_c = (m / ((1 - p) ** 2)) * ((1 - 2 * p) - + 2 * p * (x / self.chord) - - (x / self.chord) ** 2) + z_c = (m / + ((1 - p)**2)) * ((1 - 2 * p) + 2 * p * + (x / self.chord) - (x / self.chord)**2) return (z_c * self.chord) def get_thickness(x): """Return thickness from 1 'x' along the airfoil chord.""" x = 0 if x < 0 else x - z_t = 5 * t * self.chord * ( - + 0.2969 * (x / self.chord) ** 0.5 - - 0.1260 * (x / self.chord) ** 1 - - 0.3516 * (x / self.chord) ** 2 - + 0.2843 * (x / self.chord) ** 3 - - 0.1015 * (x / self.chord) ** 4) + z_t = 5 * t * self.chord * (+0.2969 * + (x / self.chord)**0.5 - 0.1260 * + (x / self.chord)**1 - 0.3516 * + (x / self.chord)**2 + 0.2843 * + (x / self.chord)**3 - 0.1015 * + (x / self.chord)**4) return z_t def get_theta(x): dz_c = float() if 0 <= x < p_c: - dz_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: - dz_c = (2 * m) / ((1 - p) ** 2) * (p - x / self.chord) + dz_c = (2 * m) / ((1 - p)**2) * (p - x / self.chord) + theta = atan(dz_c) return theta @@ -192,15 +192,14 @@ class Airfoil: sys.stdout = sys.__stdout__ print('Successfully wrote to file {}'.format(full_path)) except IOError: - print('Unable to write {} to specified directory.\n' - .format(file_name), - 'Was the full path passed to the function?') + print( + 'Unable to write {} to specified directory.\n'.format( + file_name), 'Was the full path passed to the function?') return None class Spar(Airfoil): """Contains a single spar's location.""" - def __init__(self): super().__init__() self.x_start = [] @@ -257,7 +256,6 @@ class Spar(Airfoil): class Stringer(Airfoil): """Contains the coordinates of all stringers.""" - def __init__(self): super().__init__() self.x_start = [] @@ -267,9 +265,8 @@ class Stringer(Airfoil): self.z_end = [] self.area = float() - def add_coord(self, airfoil, - stringer_u_1, stringer_u_2, - stringer_l_1, stringer_l_2): + def add_coord(self, airfoil, 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). @@ -298,8 +295,8 @@ class Stringer(Airfoil): x += interval # Add upper stringers from first spar until last spar # TODO: stringer placement if only one spar is created - interval = (airfoil.spar.x[-1][0] - - airfoil.spar.x[0][0]) / (stringer_u_2 + 1) + interval = (airfoil.spar.x[-1][0] - + airfoil.spar.x[0][0]) / (stringer_u_2 + 1) x = interval + airfoil.spar.x[0][0] for _ in range(0, stringer_u_2): i = bi.bisect_left(airfoil.x, x) @@ -317,8 +314,8 @@ class Stringer(Airfoil): self.z.append(airfoil.z[-i]) x += interval # Add lower stringers from first spar until last spar - interval = (airfoil.spar.x[-1][1] - - airfoil.spar.x[0][1]) / (stringer_l_2 + 1) + interval = (airfoil.spar.x[-1][1] - + airfoil.spar.x[0][1]) / (stringer_l_2 + 1) x = interval + airfoil.spar.x[0][1] for _ in range(0, stringer_l_2): i = bi.bisect_left(airfoil.x[::-1], x) @@ -360,16 +357,21 @@ def plot_geom(airfoil, view: False): y = [0, 0] ax.plot(x, y, linewidth='1') # Plot quarter chord - ax.plot(airfoil.chord / 4, 0, - '.', color='g', markersize=24, + ax.plot(airfoil.chord / 4, + 0, + '.', + color='g', + markersize=24, label='Quarter-chord') # Plot mean camber line - ax.plot(airfoil.x_c, airfoil.z_c, - '-.', color='r', linewidth='2', + ax.plot(airfoil.x_c, + airfoil.z_c, + '-.', + color='r', + linewidth='2', label='Mean camber line') # Plot airfoil surfaces - ax.plot(airfoil.x, airfoil.z, - color='b', linewidth='1') + ax.plot(airfoil.x, airfoil.z, color='b', linewidth='1') # Plot spars try: @@ -392,9 +394,9 @@ def plot_geom(airfoil, view: False): plot_bound = max(airfoil.x) ax.set(title='NACA ' + str(airfoil.naca_num) + ' airfoil', xlabel='X axis', - xlim=[- 0.10 * plot_bound, 1.10 * plot_bound], + xlim=[-0.10 * plot_bound, 1.10 * plot_bound], ylabel='Z axis', - ylim=[- (1.10 * plot_bound / 2), (1.10 * plot_bound / 2)]) + ylim=[-(1.10 * plot_bound / 2), (1.10 * plot_bound / 2)]) plt.grid(axis='both', linestyle=':', linewidth=1) plt.gca().set_aspect('equal', adjustable='box') |