def test_constructor_NACA4(self):
#Test NACA 4-series constructor
naca1234 = Airfoil.NACA4('1234')
wrong_naca_IDs = [
'very_wrong',
'12345',
'NACA1234',
]
for wrong_naca_ID in wrong_naca_IDs:
with self.assertRaises(NACADefintionError):
Airfoil.NACA4(wrong_naca_ID)
def test_constructor_NACA4():
"""
Test NACA 4-series constructor
"""
naca1234 = Airfoil.NACA4('1234')
wrong_naca_IDs = [
'very_wrong',
'12345',
'NACA1234',
]
for wrong_naca_ID in wrong_naca_IDs:
with pytest.raises(NACADefintionError):
Airfoil.NACA4(wrong_naca_ID)
def test_morph_new_from_two_foils(airfoil):
"""
Test that 'morph' constructor method works
"""
Airfoil.morph_new_from_two_foils(airfoil1=airfoil, airfoil2=airfoil, eta=0.5, n_points=100)
# TODO: add sensible tests here
wrong_eta_values = [
-0.1,
1.2,
]
for wrong_eta in wrong_eta_values:
with pytest.raises(ValueError):
Airfoil.morph_new_from_two_foils(airfoil1=airfoil, airfoil2=airfoil, eta=wrong_eta, n_points=100)
def test_non_monotonic_data():
x_upper = [0, +0.1, +0.1, +0.5, 1]
y_upper = [0, +0.3, +0.3, +0.2, 0]
x_lower = [0, +0.1, +0.5, 1]
y_lower = [0, -0.3, -0.2, 0]
upper = np.array([x_upper, y_upper])
lower = np.array([x_lower, y_lower])
Airfoil(upper, lower)
def updategraph(self):
print(
self.NACACONVERTER(self.MAXCAMBERSLIDER.value(),
self.MAXCAMBERPOSITIONSLIDER.value(),
self.THICKNESSSLIDER.value()))
foil = Airfoil.NACA4(
self.NACACONVERTER(self.MAXCAMBERSLIDER.value(),
self.MAXCAMBERPOSITIONSLIDER.value(),
self.THICKNESSSLIDER.value()))
foil.plot()
def make_example():
print('Create example plot... ', end='')
settings = {
'file_name': 'example.png',
'path': HERE,
}
Airfoil.NACA4('4812', n_points=300).plot(show=False,
save=True,
settings=settings)
print('Done!')
def test_reordering():
"""
Coordinates sorted from trailing edge to leading edge have to be reordered
"""
x_upper = X_UPPER[::-1]
y_upper = Y_UPPER[::-1]
x_lower = X_LOWER[::-1]
y_lower = Y_LOWER[::-1]
Airfoil((x_upper, y_upper), (x_lower, y_lower))
def test_plotting():
"""
Test plotting function
"""
settings = {
'points': True,
'camber': True,
'file_name': 'test.png',
}
file_name = Airfoil.NACA4('2412').plot(save=True, settings=settings)
assert os.path.isfile(file_name)
def compares_NACA4_with_file(self,name):
"""
Tests NACA4 airfoil computed with this module and comapres it with data
points from http://airfoiltools.com/
"""
foil = Airfoil.NACA4(name)
filename = 'naca' + name + '.dat'
path = os.path.join('airfoil_files/',filename)
precition = 6
points_from_file = np.loadtxt(path,skiprows=1)
points_from_file = np.around(points_from_file,precition)
N = len(points_from_file)
points = np.empty([N,2])
upper = True
error = []
for p in zip(points,points_from_file):
if upper:
res = foil.y_upper(p[1][0])
res_rounded = np.around(res,decimals=precition)
else:
res = foil.y_lower(p[1][0])
res_rounded = np.around(res,decimals=precition)
# Finds when to switch to lower surface
if upper and p[1][0] == 0.:
upper = False
p[0][0] = p[1][0]
p[0][1] = res_rounded
tab = np.array([p[1][0],res_rounded])
err = res_rounded - p[1][1]
error.append(err)
points_reshaped = np.reshape(points,(1,2*N))
points_from_file_reshaped = np.reshape(points_from_file,(1,2*N))
test = npt.assert_almost_equal(points,
points_from_file,
decimal=2)
# TODO: There is probably a better way
if test is None:
test = True
else:
test = False
self.assertTrue(test)
return error
def gen_airfoil(xoff, yoff, xscale=1, yscale=1):
b = np.zeros((height,width), bool)
foil = Airfoil.NACA4('4812', n_points=height)
xu = np.copy(foil._x_upper)
yu = np.copy(foil._y_upper)
xl = np.copy(foil._x_lower)
yl = np.copy(foil._y_lower)
xu *= xscale
xl *= xscale
yu *= yscale
yl *= yscale
# Set origin by shifting
xu += xoff
xl += xoff
yu += yoff
yl += yoff
foil._order_data_points()
plt.plot(xu, yu, xl, yl)
def y_up(x):
return interp1d(
xu, yu, kind="quadratic", bounds_error=False, fill_value="extrapolate"
)(x)
def y_low(x):
return interp1d(
xl, yl, kind="quadratic", bounds_error=False, fill_value="extrapolate"
)(x)
for x,y in np.ndindex(b.shape):
if float(y_low(y)) <= x <= float(y_up(y)):
b[x,y] = True
else:
b[x,y] = False
xmin, xmax = b[:,0].min(), b[:,0].max()
ymin, ymax = b[:,1].min(), b[:,1].max()
return b, xmin, xmax, ymin, ymax
def airfoil():
return Airfoil(UPPER, LOWER)
from airfoils import Airfoil
foil = Airfoil.NACA4('4812')
foil.plot()
def airfoil1():
return Airfoil.NACA4('1234')
def airfoil2():
return Airfoil.NACA4('2412')