#Wing.TR = [1.0,0.4] #Max L/D
#Wing.Fb = [0.467,1] #Max L/D
#Wing.TR = [1.0,0.2] #Max CL
#Wing.Fb = [0.53,1] #Max CL
#Wing.TR = [1.0,0.3] #Max e
#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
for i in range(len(Wing.Fb)):
if i == 0:
Wing.TR.append(1.0)
Wing.Lam.append(0.0)
Wing.Gam.append(0.0)
elif i == len(Wing.Fb) - 1:
Wing.TR.append(chord[i] / chord[i - 1])
Wing.Lam.append(10 * ARCDEG)
Wing.Gam.append(0.0)
else:
Wing.TR.append(chord[i] / chord[i - 1])
Wing.Lam.append(-3 * ARCDEG)
Wing.Gam.append(0.0)
# shiggins: this is dihedral for each section defined by Wing.Fb (invalid if ConstUpper == True)
Wing.ConstUpper = True #top surfaces of the airfoils lie against upper wing surf
#Wing.SweepFc = 0.75 # shiggins 151107: not sure how this is calculated
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)
# # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT Wing.TR = [1, 0.85, 1] Wing.Gam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG] Wing.Lam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG] Wing.Fb = [0.5, 0.9, 1] Wing.CEdge = 'LE' Wing.ConstUpper = True ############################################################################### # # Aerodynamic properties # ############################################################################### # # Set the airfoils # Wing.Airfoil = 'e423' Wing.o_eff = 0.98 Wing.FWCF = 0.98