def test_get_naca_wing(self):
dx = 0.15
c = 1.5
span = 3.0
airfoils = ['23014', '22112', '0012', '2410']
for airfoil in airfoils:
x, y, z = G.get_naca_wing(dx, airfoil, span, c)
assert not np.any(z) > (span / dx + dx)
def test_get_naca_wing(self):
dx = (10)**(np.random.uniform(-2, -1))
c = np.random.uniform(0.5, 2.0)
span = np.random.uniform(1.0, 4.0)
series = np.random.choice(
['210', '220', '230', '240', '250', '221', '231', '241', '251'])
t = np.random.randint(10, 24)
airfoil_1 = series + str(t)
camber = str(2 + np.random.randint(5)) + str(2 + np.random.randint(6))
airfoil_2 = np.random.choice(['00', camber]) + str(t)
airfoil = np.random.choice([airfoil_1, airfoil_2])
x, y, z = get_naca_wing(dx, airfoil, span, c)
count = 0
for zi in z:
if abs(zi) > (span + dx) / 2.0:
count += 1
assert count == 0