def test_RectangularWing():
"""For a simple straight wing with known area, calculate the projected
area and test the output is equal to the expected value"""
NSeg = 1
wing = LiftingSurface(ChordFunct=SimpleChordFunction,
DihedralFunct=SimpleDihedralFunction,
SweepFunct=SimpleSweepFunction,
AirfoilFunct=SimpleAirfoilFunction,
TwistFunct=SimpleTwistFunction,
ScaleFactor=5,
ChordFactor=0.2,
SegmentNo=NSeg)
# reference values (area and aspect ratio of a 5 by 1 rectangular wing)
ex_area = 5
ex_AR = 5
span = 5
# Test that the area and calculated aspect ratio are as expected
tol = 1e-5
assert (np.abs(wing.LSP_area - ex_area) < tol)
assert (np.abs(wing.AR - ex_AR) < tol)
assert (np.abs(wing.ActualSemiSpan - span) < tol)
# Also test that a multiple segment wing gives the same result
NSeg = 21
wing = LiftingSurface(ChordFunct=SimpleChordFunction,
DihedralFunct=SimpleDihedralFunction,
SweepFunct=SimpleSweepFunction,
AirfoilFunct=SimpleAirfoilFunction,
TwistFunct=SimpleTwistFunction,
ScaleFactor=5,
ChordFactor=0.2,
SegmentNo=NSeg)
assert (np.abs(wing.LSP_area - ex_area) < tol)
assert (np.abs(wing.AR - ex_AR) < tol)
assert (np.abs(wing.ActualSemiSpan - span) < tol)
def test_GenerateLeadingEdge():
# Test if GenerateLeadingEdge function matches previous version for
# the Transonic Airliner example: Note this is only to 3dp
LEPoints_ref = np.array([[0.000e+00, 0.000e+00, 0.000e+00],
[9.088e-02, 2.147e-03, 2.644e-04],
[1.752e-01, 3.580e-02, 4.508e-03],
[2.274e-01, 1.096e-01, 1.425e-02],
[2.795e-01, 1.834e-01, 2.463e-02],
[3.317e-01, 2.570e-01, 3.586e-02],
[3.838e-01, 3.304e-01, 4.815e-02],
[4.359e-01, 4.037e-01, 6.171e-02],
[4.881e-01, 4.766e-01, 7.675e-02],
[5.402e-01, 5.492e-01, 9.346e-02],
[5.924e-01, 6.213e-01, 1.121e-01],
[6.707e-01, 6.655e-01, 1.248e-01]])
# Predefined Transonic Airliner example functions used here
P = [0., 0., 0.]
NSeg = 11
Wing = LiftingSurface(P,
mySweepAngleFunctionAirliner,
myDihedralFunctionAirliner,
myTwistFunctionAirliner,
myChordFunctionAirliner,
myAirfoilFunctionAirliner,
SegmentNo=NSeg)
LEPoints = Wing.GenerateLeadingEdge()
# Test First and final point first (easier to debug)
assert (np.all(np.abs(LEPoints[1] - LEPoints_ref[1]) < 1e-3))
assert (np.all(np.abs(LEPoints[-1] - LEPoints_ref[-1]) < 1e-3))
# Now check that the entire array is less than 3 dp. out:
assert (np.all(np.abs(LEPoints - LEPoints_ref) < 1e-3))
def test_empty_liftingsurface_Build_error():
"""Tests whether building a lifting surface with undefined functional
parameters raises an error"""
with pytest.raises(AssertionError):
wing = LiftingSurface(construct_geometry=False)
# No f(eps) parameters have been defined so this should raise an error
wing.Build()
def test_SweptWing():
"""For a 15 deg swept wing with known area (unit chord, Aspect Ratio 5),
calculate the projected area and test the output is equal to the expected
value"""
NSeg = 1
LAMBDA = 15 # uniform sweep, in degrees
ScaleFactor = 5
ChordFactor = 0.2
wing = LiftingSurface(ChordFunct=SimpleChordFunction,
DihedralFunct=SimpleDihedralFunction,
SweepFunct=(lambda eps: np.ones_like(eps) * 15),
AirfoilFunct=SimpleAirfoilFunction,
TwistFunct=SimpleTwistFunction,
ScaleFactor=ScaleFactor,
ChordFactor=ChordFactor,
SegmentNo=NSeg)
# expected area = b * h, where b is the wing chord, h is the semi-span
LE_length = ScaleFactor # LE is straight: new length is 1 * ScaleFactor
span = LE_length * np.cos(np.radians(LAMBDA))
chord = ChordFactor * ScaleFactor
ex_area = chord * span
ex_AR = span / float(chord)
tol = 1e-5
assert (np.abs(wing.LSP_area - ex_area) < tol)
assert (np.abs(wing.AR - ex_AR) < tol)
assert (np.abs(wing.ActualSemiSpan - span) < tol)
def test_update_ApexPoint():
"""Tests that Build is triggered on updating Apex Point"""
# Create example airliner wing
P = (0, 0, 0)
wing = LiftingSurface(P, mySweepAngleFunctionAirliner,
myDihedralFunctionAirliner,
myTwistFunctionAirliner,
myChordFunctionAirliner,
myAirfoilFunctionAirliner)
# By adding a point to the wing, we will see if the move transformation
# has been performed when the ApexPoint attribute is changed:
from OCC.BRepBuilderAPI import BRepBuilderAPI_MakeVertex
v = BRepBuilderAPI_MakeVertex(gp_Pnt(0, 0, 0)).Vertex()
wing['test_pnt'] = v
# Updating the apex should move the surface (and test vertex) through
# the vector newApex - oldApex
wing.ApexPoint = gp_Pnt(10, 10, 10)
# Retrieve the vertex and point from the translated shape
from OCC.TopoDS import topods_Vertex
from OCC.BRep import BRep_Tool_Pnt
vout = topods_Vertex(wing['test_pnt'])
p = BRep_Tool_Pnt(vout)
# Check that the vertex was correctly transformed
xyz = [p.X(), p.Y(), p.Z()]
assert(xyz == [10, 10, 10])
# def test_Fit_BlendedTipDevice(simple_wing):
# # Fit a blended winglet to this wing and test the output
# wing = simple_wing
# wing.Fit_BlendedTipDevice(rootchord_norm=0.8, spanfraction=0.1, cant=40,
# transition=0.1, sweep=40, taper=0.7)
# # Test the (theoretical) tip chord equals the winglet root chord:
# assert((Wing.ChordFunct(1) * Wing.ScaleFactor * Wing.ChordFactor) ==
# Winglet.ChordFunct(0) * Winglet.ScaleFactor * Winglet.ChordFactor)
# # Test the length of the LE curve is the correct spanfraction
def test_update_ApexPoint():
"""Tests that Build is triggered on updating Apex Point"""
# Create example airliner wing
P = (0, 0, 0)
wing = LiftingSurface(P, mySweepAngleFunctionAirliner,
myDihedralFunctionAirliner, myTwistFunctionAirliner,
myChordFunctionAirliner, myAirfoilFunctionAirliner)
# By adding a point to the wing, we will see if the move transformation
# has been performed when the ApexPoint attribute is changed:
from OCC.BRepBuilderAPI import BRepBuilderAPI_MakeVertex
v = BRepBuilderAPI_MakeVertex(gp_Pnt(0, 0, 0)).Vertex()
wing['test_pnt'] = v
# Updating the apex should move the surface (and test vertex) through
# the vector newApex - oldApex
wing.ApexPoint = gp_Pnt(10, 10, 10)
# Retrieve the vertex and point from the translated shape
from OCC.TopoDS import topods_Vertex
from OCC.BRep import BRep_Tool_Pnt
vout = topods_Vertex(wing['test_pnt'])
p = BRep_Tool_Pnt(vout)
# Check that the vertex was correctly transformed
xyz = [p.X(), p.Y(), p.Z()]
assert (xyz == [10, 10, 10])
# def test_Fit_BlendedTipDevice(simple_wing):
# # Fit a blended winglet to this wing and test the output
# wing = simple_wing
# wing.Fit_BlendedTipDevice(rootchord_norm=0.8, spanfraction=0.1, cant=40,
# transition=0.1, sweep=40, taper=0.7)
# # Test the (theoretical) tip chord equals the winglet root chord:
# assert((Wing.ChordFunct(1) * Wing.ScaleFactor * Wing.ChordFactor) ==
# Winglet.ChordFunct(0) * Winglet.ScaleFactor * Winglet.ChordFactor)
# # Test the length of the LE curve is the correct spanfraction
def simple_wing():
"""Initialises a simple wing class, with zero twist, zero sweep, zero taper
zero dihedral, AR=5, chord=1"""
NSeg = 11
wing = LiftingSurface(ChordFunct=SimpleChordFunction,
DihedralFunct=SimpleDihedralFunction,
SweepFunct=SimpleSweepFunction,
AirfoilFunct=SimpleAirfoilFunction,
TwistFunct=SimpleTwistFunction,
ScaleFactor=5,
ChordFactor=0.2,
SegmentNo=NSeg)
return wing
def test_GenerateSectionCurves_Numpy_Functs():
"""Tests the GenerateSectionCurves function given a set of Lifting surface
functional parameters f(eps) which expects a numpy array """
def myNumpyFunct(eps):
# This will be used for twist, sweep. dihedral, and chord. returns
# an array, as eps is expected to be an array
return np.ones_like(eps) * 5
wing = LiftingSurface(construct_geometry=False)
wing.ChordFunct = myNumpyFunct
wing.SweepFunct = myNumpyFunct
wing.DihedralFunct = myNumpyFunct
wing.TwistFunct = myNumpyFunct
wing.AirfoilFunct = myAirfoilFunctionAirliner # Builtin example
wing.GenerateSectionCurves()
assert (len(wing._Sections) > 0)
def test_GenerateSectionCurves_NonNumpy_ChordFunct():
"""Tests the GenerateSectionCurves function given a set of Lifting surface
functional parameters f(eps) which expects a single input (and output) """
def mySingleInputFunct(eps):
# This will be used for twist, sweep. dihedral, and chord. Returns a
# single value, as eps is expected to be a single value
return 5
wing = LiftingSurface(construct_geometry=False)
wing.ChordFunct = mySingleInputFunct
wing.SweepFunct = mySingleInputFunct
wing.DihedralFunct = mySingleInputFunct
wing.TwistFunct = mySingleInputFunct
wing.AirfoilFunct = myAirfoilFunctionAirliner # Builtin example
wing.GenerateSectionCurves()
assert (len(wing._Sections) > 0)
def test_GenerateSectionCurves_Numpy_Functs():
"""Tests the GenerateSectionCurves function given a set of Lifting surface
functional parameters f(eps) which expects a numpy array """
def myNumpyFunct(eps):
# This will be used for twist, sweep. dihedral, and chord. returns
# an array, as eps is expected to be an array
return np.ones_like(eps) * 5
wing = LiftingSurface(construct_geometry=False)
wing.ChordFunct = myNumpyFunct
wing.SweepFunct = myNumpyFunct
wing.DihedralFunct = myNumpyFunct
wing.TwistFunct = myNumpyFunct
wing.AirfoilFunct = myAirfoilFunctionAirliner # Builtin example
wing.GenerateSectionCurves()
assert(len(wing._Sections) > 0)
def test_GenerateSectionCurves_NonNumpy_ChordFunct():
"""Tests the GenerateSectionCurves function given a set of Lifting surface
functional parameters f(eps) which expects a single input (and output) """
def mySingleInputFunct(eps):
# This will be used for twist, sweep. dihedral, and chord. Returns a
# single value, as eps is expected to be a single value
return 5
wing = LiftingSurface(construct_geometry=False)
wing.ChordFunct = mySingleInputFunct
wing.SweepFunct = mySingleInputFunct
wing.DihedralFunct = mySingleInputFunct
wing.TwistFunct = mySingleInputFunct
wing.AirfoilFunct = myAirfoilFunctionAirliner # Builtin example
wing.GenerateSectionCurves()
assert(len(wing._Sections) > 0)
if __name__ == "__main__":
from OCC.Display.SimpleGui import init_display
display, start_display, add_menu, add_function_to_menu = init_display()
# Generate a wing first to attach the engine to
P = (0, 0, 0)
SegmentNo = 10
ChordFactor = 1
ScaleFactor = 44.56
Wing = LiftingSurface(P, wingex.mySweepAngleFunctionAirliner,
wingex.myDihedralFunctionAirliner,
wingex.myTwistFunctionAirliner,
wingex.myChordFunctionAirliner,
wingex.myAirfoilFunctionAirliner,
SegmentNo=SegmentNo,
ChordFactor=ChordFactor,
ScaleFactor=ScaleFactor)
Wing.Display(display)
SpanStation = 0.3 # The engine is to be placed at 30% span
EngineDia = 2.9
NacelleLength = 1.95*EngineDia
EngineSection, HChord = act.CutSect(Wing['Surface'], SpanStation)
Chord = HChord.GetObject()
CEP = Chord.EndPoint()
display.DisplayShape(Chord, update=True, color='black')
# Variables controlling the position of the engine with respect to the wing
EngineCtrFwdOfLE = 0.98
def test_default_args():
"""Tests that the default arguments do not raise an error. Note that
no default surface is expected to be generated however"""
wing = LiftingSurface()
assert (len(wing) == 0)
assert (len(wing.Sections) == 0)
def test_empty_liftingsurface():
"""Tests that construction"""
wing = LiftingSurface(construct_geometry=False)
def example_topos(request):
"""Return both the topology object and the resulting string for a set of
topologies"""
topo_type = request.param[0]
if topo_type == 'conventional':
# Create mock components, without generating any geometry
fus = Fuselage(construct_geometry=False)
fin = LiftingSurface(construct_geometry=False)
tailplane = LiftingSurface(construct_geometry=False)
mirror_pln = gp_Ax2()
wing = LiftingSurface(construct_geometry=False)
engine = Engine(construct_geometry=False)
# For now we must manually add parts and affinities
topo = Topology()
topo.AddPart(fus, 'Fuselage', 3)
topo.AddPart(fin, 'fin', 0)
topo.AddPart(mirror_pln, 'mirror_pln', 0)
topo.AddPart(tailplane, 'tailplane', 0)
topo.AddPart(wing, 'wing', 1)
topo.AddPart(engine, 'engine', 0)
if topo_type == 'thunderbolt_a10':
fus = Fuselage(construct_geometry=False)
mirror_pln = gp_Ax2()
engine = Engine(construct_geometry=False)
wing = LiftingSurface(construct_geometry=False)
tailplane = LiftingSurface(construct_geometry=False)
tail_fin = LiftingSurface(construct_geometry=False)
topo = Topology()
topo.AddPart(fus, 'Fuselage', 3)
topo.AddPart(mirror_pln, 'mirror', 0)
topo.AddPart(engine, 'powerplant', 0)
topo.AddPart(tailplane, 'Tailplane', 1)
topo.AddPart(tail_fin, "Tail fin", 0)
topo.AddPart(wing, "wing", 0)
if topo_type == 'predator':
# Create mock components, without generating any geometry
fus = Fuselage(construct_geometry=False)
engine = Engine(construct_geometry=False)
fin = LiftingSurface(construct_geometry=False)
mirror_pln = gp_Ax2()
wing = LiftingSurface(construct_geometry=False)
Vfin = LiftingSurface(construct_geometry=False)
# For now we must manually add parts and affinities
topo = Topology()
topo.AddPart(fus, 'Fuselage', 4)
topo.AddPart(engine, 'engine', 0)
topo.AddPart(fin, 'fin', 0)
topo.AddPart(mirror_pln, 'mirror_pln', 0)
topo.AddPart(wing, 'wing', 0)
topo.AddPart(Vfin, 'V-Fin', 0)
if topo_type == 'proteus':
fus = Fuselage(construct_geometry=False)
mirror_pln = gp_Ax2()
engine = Engine(construct_geometry=False)
wing = LiftingSurface(construct_geometry=False)
wing_in = LiftingSurface(construct_geometry=False)
tailplane = LiftingSurface(construct_geometry=False)
pod = Fuselage(construct_geometry=False)
finup = LiftingSurface(construct_geometry=False)
findown = LiftingSurface(construct_geometry=False)
wing_out = LiftingSurface(construct_geometry=False)
topo = Topology()
topo.AddPart(fus, 'Fuselage', 3)
topo.AddPart(mirror_pln, 'mirror', 0)
topo.AddPart(engine, 'powerplant', 0)
topo.AddPart(wing, "wing", 0)
topo.AddPart(wing_in, "TP/inbbd wing", 1)
topo.AddPart(pod, 'Pod/tail boom', 3)
topo.AddPart(wing_out, "outbd wing", 0)
topo.AddPart(finup, "Fin (up)", 0)
topo.AddPart(findown, "Fin (dwn)", 0)
return topo, request.param[1]
