#===============================================================================
#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
#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]
# 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.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 Wing.o_eff = 0.98 # Oswald Efficiency