Aircraft = ACTailAircraft() Aircraft.name = 'Tutorial Aircraft' # # Assign the already generated parts # Aircraft.SetFuselage(Fuselage) Aircraft.SetPropulsion(Propulsion) Aircraft.SetWing(Wing) # # Aircraft Properties # Aircraft.TotalWeight = 28 * LBF Aircraft.TippingAngle = 10 * ARCDEG Aircraft.RotationAngle = 10 * ARCDEG Aircraft.Alpha_Groundroll = 0 * ARCDEG # incidence on wing Aircraft.CMSlopeAt = (0 * ARCDEG, 3 * ARCDEG) #plotting Aircraft.CLSlopeAt = (6 * ARCDEG, 7 * ARCDEG) #plotting Aircraft.CLHTSlopeAt = (0 * ARCDEG, 9 * ARCDEG) #plotting Aircraft.DWSlopeAt = (7 * ARCDEG, 8 * ARCDEG) #plotting Aircraft.Alpha_Zero_CM = 0 * ARCDEG Aircraft.StaticMargin = 0.1 # # Maximum velocity for plotting purposes # Aircraft.VmaxPlt = 100 * FT / SEC
# Assign the already generated parts Aircraft.SetFuselage(Fuselage) Aircraft.SetPropulsion(Propulsion) Aircraft.SetWing(Wing) # # Position the wing on the top of the fuselage Aircraft.WingFuseFrac = 0.3 Aircraft.Wing.i = 0 * ARCDEG # # Aircraft Properties # Total weight is going to change 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
Aircraft.WingFuseFrac = 0 # 0.0 @ bottom of fuselage; 1.0 @ top of fuselage
Aircraft.Wing.i = 0 * ARCDEG # induced angle of attack, wing incidence
#Aircraft.Wing.X[0] = 20*IN
# Engine alignment (height)
Aircraft.EngineAlign = 0.72 #this doesnt seem to be doing anything
# Aircraft Properties
EmptyWeight = 17 * LBF # dechellis: estimated airframe weight
TennisBalls = 60.0 # dechellis: number of tennis balls flying
BallWeight = 0.131333 * LBF # dechellis: weight of 1 tennis ball
PayloadWeight = (0.50 * LBF +
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