def _BuildSurfacePoints(self, ChordFactor, ScaleFactor):
LEPoints = self._GenerateLeadingEdge()
SurfacePntsUp = []
SurfacePntsDown = []
Sections = []
# SurfacePntstoAdd=[]
Eps = np.linspace(0, 1, self.NPaero_span + 1)
Sections = [
self.AirfoilFunct(Eps[i], LEPoints[i], self.ChordFunct,
ChordFactor, self.DihedralFunct,
self.TwistFunct).Curve
for i in xrange(self.NPaero_span + 1)
]
numb = 0
for num in xrange(self.NPaero_span + 1):
section = Sections[num]
sectionPnt = act.Uniform_Points_on_Curve(section,
self.NPaero_chord)
numb = numb + 1
for numm in xrange(1, self.NPaero_chord + 1):
print(sectionPnt[numm - 1].Y())
print(sectionPnt[numm - 1].X())
edgePnts = act.make_vertex(sectionPnt[numm - 1])
if self.ScaleFactor != 1:
Origin = gp_Pnt(0., 0., 0.)
Pnts = act.scale_uniformal(edgePnts, Origin,
self.ScaleFactor)
if numm <= (self.NPaero_chord - 1) / 2 + 1:
SurfacePntsUp.append(Pnts)
if numm == (self.NPaero_chord - 1) / 2 + 1:
SurfacePntsDown.append(Pnts)
elif numm > (self.NPaero_chord - 1) / 2 + 1:
# SurfacePntsDown.append(SurfacePntstoAdd)
SurfacePntsDown.append(Pnts)
# SurfacePntsDown=SurfacePntsD+SurfacePntstoAdd
# numbb=numbb+1
# if self.ScaleFactor!= 1:
# Origin = gp_Pnt(0., 0., 0.)
# SurfacePnts=act.scale_uniformal(SurfacePnts, Origin, self.ScaleFactor)
print(np.shape(SurfacePntsUp))
print(np.shape(SurfacePntsDown))
return SurfacePntsUp, SurfacePntsDown
def _BuildLS(self, ChordFactor, ScaleFactor):
"""Generates a tentative lifting surface, given the general,
nondimensional parameters of the object (variations of chord length,
dihedral, etc.) and the two scaling factors.
Parameters
----------
ChordFactor - float
Factor againt which the standard shape is scaled in the chordwise
direction
ScaleFactor - float
Factor againt which the standard shape is scaled in the world
coordinates
Returns
-------
LS : TopoDS_Shape
The generated Lifting surface
ActualSemiSpan : scalar
TODO: currently not calculated, None is returned
LSP_area : scalar
TODO: currently not calculated, None is returned
AR : scalar
TODO: currently not calculated, None is returned
WingTip : TopoDS face or shape
TODO: currently not calculated, None is returned
"""
LEPoints = self._GenerateLeadingEdge()
Sections = []
# TODO: These lists are used for when the curve has been smoothed or
# the loft has failed, neither of which have been implemented yet
# ProjectedSections = []
# TEPoints_u = []
# TEPoints_l = []
Eps = np.linspace(0, 1, self.SegmentNo + 1)
Sections = [
self.AirfoilFunct(Eps[i], LEPoints[i], self.ChordFunct,
ChordFactor, self.DihedralFunct,
self.TwistFunct).Curve
for i in xrange(self.SegmentNo + 1)
]
self._Sections = Sections # I used from debugging - remove it?
# TODO: Implement chord projection and Curve start/end points
# to rescale smoothed curves and for secondary loft methods
LS = act.AddSurfaceLoft(Sections,
max_degree=self._max_degree,
continuity=self._Cont)
if LS is None:
pass
WingTip = None
if self.TipRequired:
pass
# Scaling
if self.ScaleFactor != 1:
Origin = gp_Pnt(0., 0., 0.)
LS = act.scale_uniformal(LS, Origin, self.ScaleFactor)
# TODO: Wing tip scaling (TipRequired is not implemented yet)
if self.TipRequired and WingTip:
pass
self.RootChord = (self.ChordFunct(0) * ChordFactor) * ScaleFactor
# Temporarily set other variables as None until above TODO's are done
ActualSemiSpan = None
LSP_area = None
AR = None
return LS, ActualSemiSpan, LSP_area, AR, WingTip
