Python ACMainWing.TR Examples

Example #1

#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)

Example #2

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
#

Example #3

###############################################################################
#
# 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

Example #4

###############################################################################
#
# 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

Example #5

File: wing_matt.py Project: Aerothon-2020/TutorialAircraft

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

Example #6

###############################################################################
#
# 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

Example #7

File: Wing.py Project: Aerothon-2020/Adv2020Aircraft

###############################################################################
#
# 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

Example #8

###############################################################################
#
# 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