def test_Selig_Airfoil_Assertions():
# Test that a non-string raises a type error
with pytest.raises(TypeError):
Af = Airfoil(SeligProfile=100)
# Test that a non existant Selig Airfoil raises an error
with pytest.raises(AssertionError):
Af = Airfoil(SeligProfile='SomeImaginaryAirfoil')
def my_InterpAirfoilFunction_multiple(eps):
# I'll use three airfoil sections, located at eps=0, eps=0.5, eps=1.
# Currently, this is safest using airfoils with equal numbers of points,
# TODO: make this work for non-matching numbers of points (cubic interp?)
af_1 = Airfoil(Naca4Profile='0012')
af_2 = Airfoil(Naca4Profile='0025')
af_3 = Airfoil(Naca4Profile='2408')
if eps < 0.5:
profile_dict = {
'InterpProfile': True,
'Epsilon': eps,
'Af1': af_1,
'Af2': af_2,
'Eps1': 0,
'Eps2': 0.5
}
elif eps <= 1:
profile_dict = {
'InterpProfile': True,
'Epsilon': eps,
'Af1': af_2,
'Af2': af_3,
'Eps1': 0.5,
'Eps2': 1
}
return profile_dict
def test_CRM_Airfoil_Assertions():
# Test that an out of range epsilon produces an error
with pytest.raises(AssertionError):
Af = Airfoil(CRM_Epsilon=10)
# Test that a string containing letters con raises a type error
with pytest.raises(ValueError):
Af = Airfoil(CRM_Epsilon='d')
def test_Airfoil_manual(airfoil_examples):
# Unwrap parametrised arguments from the pytest.fixture
ProfileType, Profile = airfoil_examples
Af = Airfoil()
# This is probably a dirty way of doing this, but couldn't think of another
if ProfileType == 'Naca4Profile':
Af.AddNACA4(Profile)
elif ProfileType == 'SeligProfile':
Af.AddAirfoilFromSeligFile(Profile)
elif ProfileType == 'CRM_Epsilon':
Af.AddCRMLinear(Profile)
else:
raise NotImplementedError(
'{} is not an Implemented Airfoil type'.format(ProfileType))
# Test the Airfoil.Profile is the expected dictionary
assert (ProfileType in Af.Profile.keys())
assert (Af.Profile[ProfileType] == str(Profile))
# Test the Curve has been generated
assert (Af.Curve is not None)
# Test the python-occ spline object:
assert (type(Af.Curve) == OCC.Geom.Handle_Geom_BSplineCurve)
assert (Af.Curve.IsNull() == False)
# Check the Trailing Edge X is roughly equal to the chord length
start_pt = get_Airfoil_startpoint(Af)
assert ((np.abs(start_pt[0] - Af.ChordLength) / Af.ChordLength) < 0.01)
def test_Airfoil_emptystring():
# Test that an empty profile string creates an 'empty' airfoil
Af = Airfoil(Naca4Profile='')
assert (not Af.Curve)
# Also check Selig airfoils:
Af = Airfoil(SeligProfile='')
assert (not Af.Curve)
def my_InterpAirfoilFunction(eps):
af_root = Airfoil(Naca4Profile='0012')
af_tip = Airfoil(Naca4Profile='0025')
profile_dict = {
'InterpProfile': True,
'Epsilon': eps,
'Af1': af_root,
'Af2': af_tip,
'Eps1': 0,
'Eps2': 1
}
return profile_dict
def myAirfoilFunction(eps):
af_root = Airfoil(SeligProfile='naca63a418')
af_tip = Airfoil(SeligProfile='naca63a412')
profile_dict = {
'InterpProfile': True,
'Epsilon': eps,
'Af1': af_root,
'Af2': af_tip,
'Eps1': 0,
'Eps2': 1
}
return profile_dict
def test_Null_Airfoil():
# Generate Empty Airfoil
Af = Airfoil()
assert (Af.LE == [0., 0., 0.])
assert (Af.Rotation == 0)
assert (Af.Twist == 0)
assert (Af.ChordLength == 1)
assert (Af.Profile is None)
assert (Af.Curve is None)
def test_nonzero_rotation():
# Use Start Point of untwisted, unrotated, unit chord, LE in origin NACA4
# Airfoil as reference
default_SP = np.array([1., 0., 0.00126])
# Test Non-Zero Rotation (Around X axis):
Af = Airfoil(ChordLength=1, Naca4Profile='0012', Rotation=10)
start_pt = get_Airfoil_startpoint(Af)
# Miscellaneous function for creating rotation matrix of th around X axis
gamma = Af.Rotation * np.pi / 180.
SP_ref = roll_matrix(gamma).dot(default_SP)
assert (np.all((start_pt - SP_ref) < 1e-10))
def test_nonzero_twist():
# Use Start Point of untwisted, unrotated, unit chord, LE in origin NACA4
# Airfoil as reference
default_SP = np.array([1., 0., 0.00126])
# Test Non-zero Twist (around Y axis):
Af = Airfoil(ChordLength=1, Naca4Profile='0012', Twist=10)
start_pt = get_Airfoil_startpoint(Af)
beta = Af.Twist * np.pi / 180.
SP_ref = twist_matrix(-beta).dot(default_SP)
assert (np.all((start_pt - SP_ref) < 1e-10))
def test_nonzero_LE():
# Use Start Point of untwisted, unrotated, unit chord, LE in origin NACA4
# Airfoil as reference
default_SP = np.array([1., 0., 0.00126])
# Non-Zero leading edge:
Af = Airfoil(LeadingEdgePoint=[1., 1., 1.],
ChordLength=1,
Naca4Profile='0012')
start_pt = get_Airfoil_startpoint(Af)
SP_ref = default_SP + np.array([1., 1., 1.])
assert (np.all((start_pt - SP_ref) < 1e-10))
def test_Transform_Airfoil():
# Use Start Point of untwisted, unrotated, unit chord, LE in origin NACA4
# Airfoil as reference
default_SP = np.array([1., 0., 0.00126])
# Test Translation, Rotation and Twist :
Af = Airfoil(LeadingEdgePoint=[1., 1., 1.],
ChordLength=1,
Naca4Profile='0012',
Rotation=10,
Twist=5)
start_pt = get_Airfoil_startpoint(Af)
beta = Af.Twist * np.pi / 180.
gamma = Af.Rotation * np.pi / 180.
Yrot_mat = twist_matrix(-beta)
Xrot_mat = roll_matrix(gamma)
rotation = Yrot_mat.dot(Xrot_mat)
SP_ref = rotation.dot(default_SP) + np.array([1., 1., 1.])
assert (np.all((start_pt - SP_ref) < 1e-10))
def test_overdefined_Airfoil():
# Test that two or more specified profiles raises an error
with pytest.raises(AssertionError):
Af = Airfoil(SeligProfile='b707a', Naca4Profile='0012')