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-rw-r--r--tools/creator.py72
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')
Copyright 2019--2024 Marius PETER