#Wing.Fb = [0.467,1] #Max e
#===============================================================================
#
#===============================================================================
Wing.Gam = [ 0*ARCDEG,0*ARCDEG]
Wing.Lam = [ 0*ARCDEG,0*ARCDEG]
#Wing.SweepFc = 0.5
#Wing.CEdge = 'LE' #LE of wing to be tapered or constant LE
Wing.ConstUpper = False
#
# Add Vertical Winglets
Wing.AddWinglet("Winglet",2)
Winglet = Wing.Winglets.Winglet
#
Winglet.b = 6 *IN
Winglet.Airfoil = 'NACA0006'
Winglet.Lam = [0*ARCDEG, 0*ARCDEG]
Winglet.Gam = [0*ARCDEG, 0*ARCDEG]
Winglet.Fb = [0.1, 1.0]
Winglet.TR = [.9, 0.05]
Winglet.SweepFc = 0.9
Winglet.Symmetric = True
Winglet.FullWing = True
#
#Winglet.SetWeightCalc(ACSolidWing)
#Winglet.WingWeight.WingMat = PinkFoam.copy()
Wing.CEdge = 'LE' #LE of wing to be tapered or constant LE, shiggins 151107: will override LAM
#==============================================================================#
# Aerodynamic properties
#==============================================================================#
# Finite wing correction factor: make 2D airfoil data match the 3D wing profile
Wing.FWCF = 0.98
# Oswald efficiency
Wing.o_eff = 0.97
# Polar slope evaluations
Wing.ClSlopeAt = (0 * ARCDEG, 7 * ARCDEG)
Wing.CmSlopeAt = (0 * ARCDEG, 7 * ARCDEG)
Wing.AddWinglet('Winglet', 1)
Winglet = Wing.Winglets.Winglet
Winglet.b = 10 * IN
#Winglet.Airfoil = 'S1223_TC'
Winglet.Airfoil = 'NACA0006'
Winglet.Lam = [0 * ARCDEG, 0 * ARCDEG]
Winglet.Gam = [0 * ARCDEG, 0 * ARCDEG]
Winglet.Fb = [0.1, 1]
Winglet.TR = [1, 0.1]
Winglet.SweepFc = .88
Winglet.Symmetric = True
Winglet.FullWing = True
#
Winglet.SetWeightCalc(ACSolidWing)
Winglet.WingWeight.WingMat = Basswood.copy()