#Wing.S = 22*FT**2 # wing surface area
# More realistic 12 ft wing
Wing.b = 144 * IN # wing span
Wing.S = 18 * FT**2 # wing surface area
Wing.FullWing = True
# Wing Chord vs Position
# Box Wing
Wing.Fb = [1.0] # Wingspan Position (0 to 1)
chord = [1.0] # Chord at Position with relation to nominal chord
# Tapered Wing
#Wing.Fb = [0.2, 1.0] # Wingspan Position (0 to 1)
#chord = [1.10, 0.8] # Chord at Position with relation to nominal chord
Wing.TR = []
Wing.Gam = []
Wing.Lam = []
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)
Wing.Alt_LO = 920 * FT #Wing.AR = 5.0 Wing.b = 95 * IN ############################################################################### # # 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 #
############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 6*FT #Wing.LowerWing.b = 6*FT #=============================================================================== #b=150,S=3200 #=============================================================================== Wing.TR = [1.0,0.5] #Taper Ratio Wing.Fb = [0.50,1.0] #Span Fraction #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
############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT #=============================================================================== #b=150,S=3200 #=============================================================================== Wing.TR = [1.0, 0.55] #Increased from MAX L/D to increase root induced aoa Wing.Fb = [0.46667, 1] #Original #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.Lift_LO = 60 * LBF # Desired lift at liftoff Wing.V_max_climb = 65 * FT / SEC # liftoff speed Wing.Alt_LO = 200 * FT # liftoff altitude Wing.AR = 8.0 # Aspect Ratio Wing.b = 12 * 12 * IN # Wingspan ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True Wing.Fb = [0.4, 0.8, 1] # Span fraction corresponding to inputs below Wing.TR = [1, 0.8, .7] # Taper ratio Wing.Gam = [20 * ARCDEG, 20 * ARCDEG, 20 * ARCDEG] # Dihedral Wing.Lam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG] # wing sweep angles Wing.CEdge = 'LE' # Defines constant edge Wing.ConstUpper = True ############################################################################### # # Aerodynamic properties # ############################################################################### # # Set the airfoils # Wing.Airfoil = 'CLi4005b' # Chooses airfoil from /AircraftDesign/Airfoils.. just load in normal .dat files like you would to xflr5
############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT #=============================================================================== #b=150,S=3200 #=============================================================================== Wing.TR = [1.0, 0.47] #Edited by Brock Pleiman 10/11/13 Wing.Fb = [0.545, 1.0] #Edited by Brock Pleiman 10/11/13 #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
############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 6*FT #Wing.LowerWing.b = 6*FT #=============================================================================== #b=150,S=3200 #=============================================================================== Wing.TR = [1.0,0.7] #Taper Ratio Wing.Fb = [0.598,1.0] #Span Fraction #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
############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 6*FT #Wing.LowerWing.b = 6*FT #=============================================================================== #b=150,S=3200 #=============================================================================== Wing.TR = [1.0, 0.01] #Taper Ratio Wing.Fb = [0.01, 1.0] #Span Fraction #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 = [50 * ARCDEG, 50 * ARCDEG] #Wing.SweepFc = 0