def myAirfoilFunctionBoxWing(Epsilon, LEPoint, ChordFunct, ChordFactor,
DihedralFunct, TwistFunct):
# Defines the variation of cross section as a function of Epsilon
AirfoilChordLength = (ChordFactor*ChordFunct(Epsilon)) / \
np.cos(np.radians(TwistFunct(Epsilon)))
SmoothingPasses = 1
Camber1 = 5.0
Camber2 = -5.0
Transition1 = 0.45
Transition2 = 0.55
# Known values of dihedral at start, transition and end locations
EpsArray = np.array([0, Transition1, Transition2, 1])
CamberArray = np.array([Camber1, Camber1, Camber2, Camber2])
Camber = np.interp(Epsilon, EpsArray, CamberArray)
prof = str(int(round(Camber))) + '310'
Af = primitives.Airfoil(LEPoint,
AirfoilChordLength,
DihedralFunct(Epsilon),
TwistFunct(Epsilon),
Naca4Profile=prof)
return Af
def SimpleAirfoilFunction(Epsilon, LEPoint, ChordFunct, ChordFactor,
DihedralFunct, TwistFunct):
"""constant cross section with Epsilon"""
AfChord = ChordFunct(Epsilon) * ChordFactor
Af = primitives.Airfoil(LEPoint, ChordLength=AfChord,
Rotation=DihedralFunct(Epsilon),
Twist=TwistFunct(Epsilon),
Naca4Profile='0012')
return Af
def myAirfoilFunctionAirliner(Epsilon, LEPoint, ChordFunct, ChordFactor,
DihedralFunct, TwistFunct):
"""Defines the variation of cross section as a function of Epsilon"""
AfChord = ((ChordFactor*ChordFunct(Epsilon)) /
np.cos(np.radians(TwistFunct(Epsilon))))
Af = primitives.Airfoil(LEPoint, ChordLength=AfChord,
Rotation=DihedralFunct(Epsilon),
Twist=TwistFunct(Epsilon),
CRMProfile=True, CRM_Epsilon=Epsilon)
return Af
def myAirfoilFunctionTP(Epsilon, LEPoint, ChordFunct, ChordFactor,
DihedralFunct, TwistFunct):
"""Defines the variation of cross section as a function of Epsilon"""
AirfoilChordLength = (ChordFactor * ChordFunct(Epsilon) /
np.cos(np.radians(TwistFunct(Epsilon))))
AirfoilSeligName = 'sc20010'
# TODO : SmoothingPasses = 3
Af = primitives.Airfoil(LEPoint,
ChordLength=AirfoilChordLength,
Rotation=DihedralFunct(Epsilon),
Twist=TwistFunct(Epsilon),
SeligProfile=AirfoilSeligName)
return Af
# ==============================================================================
# Example: airfoil from Selig-formatted coordinate file. Leading edge point
# in origin, unit chord along x axis, no rotation around the x or y axes.
# Coordinates for Drela DAE11 low Reynolds number section, two smoothing
# iterations.
# ==============================================================================
LEPoint = [0., 0., 0.]
ChordLength = 1
Rotation = 0
Twist = 0
AirfoilSeligName = 'dae11'
# SmoothingPasses = 1 #TODO
# Instantiate class to set up a generic airfoil with these basic parameters
Af = primitives.Airfoil(LEPoint, ChordLength, Rotation, Twist,
SeligProfile=AirfoilSeligName)
display.DisplayShape(Af.Curve, update=True)
display.DisplayShape(Af.ChordLine, update=True, color='black')
start_display()
# If using interactive mode i.e. ipython, Airfoil can be removed with:
# display.Context.Erase(Af1_disp.GetObject().GetHandle())
# Af1.Curve.GetObject().Delete() # Not sure if this truly collects the garbage yet
#
# # Or Clear the display:
# display.EraseAll()