Ejemplo n.º 1
0
                 BallWeight) * TennisBalls  # dechellis: "passenger luggage"
Fuselage.PayBay.TennisBalls.Weight = BallWeight * TennisBalls  # Reassign tennis ball weight distribution based off desired loading
Aircraft.TotalWeight = PayloadWeight + EmptyWeight  # needed for calculations
Aircraft.TippingAngle = 10 * ARCDEG  # Black line on AC plot, set to Lift Off AoA
Aircraft.RotationAngle = 8.8 * ARCDEG  # Red line on AC plot, recommend 15 deg
Aircraft.Alpha_Groundroll = 0 * ARCDEG  # AOA during ground roll

Aircraft.CMSlopeAt = (2 * ARCDEG, 10 * ARCDEG)  # shiggins: what does this do?
Aircraft.CLSlopeAt = (3 * ARCDEG, 14 * ARCDEG)  # shiggins: what does this do?
Aircraft.CLHTSlopeAt = (-5 * ARCDEG, 10 * ARCDEG
                        )  # shiggins: what does this do?
Aircraft.DWSlopeAt = (3 * ARCDEG, 15 * ARCDEG)  # shiggins: what does this do?

Aircraft.Alpha_Zero_CM = 5.0 * ARCDEG  # for steady level flight
Aircraft.StaticMargin = 0.005  # this is driving wing position (higher values move the wing farther aft)
Aircraft.WingXMaxIt = 60  # this is the no. of iterations to solve

Aircraft.VmaxPlt = 100 * FT / SEC  # Maximum velocity for plotting purposes

Aircraft.RotationTime = 0.5 * SEC  # Est time aircraft rotates on ground during takeoff

Aircraft.NoseGearOffset = 0.12 * M
#==============================================================================#
# HORIZONTAL TAIL
#==============================================================================#
HTail = Aircraft.HTail  # set up the horizontal tail class
HTail.Airfoil = 'NACA0012'

Aircraft.HTailPos = 0.0  # T-Tail = 1 (horiz tail at top of vert tail);
# reg    = 0 (horiz tail at same lvl as middle of tail bulk)
Ejemplo n.º 2
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Aircraft.TotalWeight = 54 * LBF
# Engine align
Aircraft.EngineAlign = 0

Aircraft.TippingAngle = 15 * ARCDEG  # Black line on AC plot
Aircraft.RotationAngle = 12 * ARCDEG  # Red line on AC plot
Aircraft.Alpha_Groundroll = 0 * ARCDEG

Aircraft.CMSlopeAt = (0 * ARCDEG, 10 * ARCDEG)
Aircraft.CLSlopeAt = (0 * ARCDEG, 15 * ARCDEG)
Aircraft.CLHTSlopeAt = (0 * ARCDEG, 15 * ARCDEG)
Aircraft.DWSlopeAt = (0 * ARCDEG, 15 * ARCDEG)

Aircraft.Alpha_Zero_CM = 3.0 * ARCDEG  #for steady level flight
Aircraft.StaticMargin = 0.05  # Location of Wing
Aircraft.WingXMaxIt = 50
Aircraft.WingXOmega = 1
#
# Maximum velocity for plotting purposes
Aircraft.VmaxPlt = 75 * FT / SEC
#
# Estimate for the time the aircraft rotates on the ground during takeoff
Aircraft.RotationTime = 0.5 * SEC

Aircraft.NoseGearOffset = 9 * IN
###############################################################################
#
# Tail surfaces
#
###############################################################################
Ejemplo n.º 3
0
                 BallWeight) * TennisBalls  # dechellis: "passenger luggage"
Fuselage.PayBay.TennisBalls.Weight = BallWeight * TennisBalls  # Reassign tennis ball weight distribution based off desired loading
Aircraft.TotalWeight = PayloadWeight + EmptyWeight  # needed for calculations
Aircraft.TippingAngle = 10 * ARCDEG  # Black line on AC plot, set to Lift Off AoA
Aircraft.RotationAngle = 15 * ARCDEG  # Red line on AC plot, recommend 15 deg
Aircraft.Alpha_Groundroll = 0 * ARCDEG  # AOA during ground roll

Aircraft.CMSlopeAt = (2 * ARCDEG, 10 * ARCDEG)  # shiggins: what does this do?
Aircraft.CLSlopeAt = (3 * ARCDEG, 14 * ARCDEG)  # shiggins: what does this do?
Aircraft.CLHTSlopeAt = (-5 * ARCDEG, 10 * ARCDEG
                        )  # shiggins: what does this do?
Aircraft.DWSlopeAt = (3 * ARCDEG, 15 * ARCDEG)  # shiggins: what does this do?

Aircraft.Alpha_Zero_CM = 5.0 * ARCDEG  # for steady level flight
Aircraft.StaticMargin = 0.1  # shiggins: this is driving wing position (higher values move the wing farther aft)
Aircraft.WingXMaxIt = 60  # shiggins: this is the no. of iterations to solve

Aircraft.VmaxPlt = 60 * FT / SEC  # Maximum velocity for plotting purposes

Aircraft.RotationTime = 0.5 * SEC  # Est time aircraft rotates on ground during takeoff

#==============================================================================#
# HORIZONTAL TAIL
#==============================================================================#
HTail = Aircraft.HTail  # set up the horizontal tail class
HTail.Airfoil = 'NACA0012'

Aircraft.HTailPos = 0.0  # T-Tail = 1 (horiz tail at top of vert tail);
# reg    = 0 (horiz tail at same lvl as middle of tail bulk)

HTail.FullWing = True  # Full wing surface (i.e. top and bottom tail)