# 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 # # Estimate for the time the aircraft rotates on the ground during takeoff Aircraft.RotationTime = 0.5 * SEC Aircraft.NoseGearOffset = 9 * IN
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 Aircraft.RotationTime = 0.5 * SEC # Est time aircraft rotates on ground during takeoff Aircraft.NoseGearOffset = 0.12 * M #==============================================================================# # HORIZONTAL TAIL
# 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 ############################################################################### # # Tail surfaces #
# Aircraft.WingFuseFrac = 1.05 Aircraft.Wing.i = 0 * ARCDEG # # Aircraft Properties # Total weight is going to change Aircraft.TotalWeight = 27 * LBF # Engine align Aircraft.EngineAlign = 1.0 Aircraft.TippingAngle = 8.5 * ARCDEG # Black line on AC plot, set to Lift Off AoA Aircraft.RotationAngle = 15 * ARCDEG # Red line on AC plot, set 15 deg Aircraft.Alpha_Groundroll = 0 * ARCDEG Aircraft.CMSlopeAt = (2 * ARCDEG, 10 * ARCDEG) Aircraft.CLSlopeAt = (3 * ARCDEG, 14 * ARCDEG) Aircraft.CLHTSlopeAt = (-5 * ARCDEG, 10 * ARCDEG) Aircraft.DWSlopeAt = (3 * ARCDEG, 15 * ARCDEG) Aircraft.Alpha_Zero_CM = 3.0 * ARCDEG #for steady level flight Aircraft.StaticMargin = 0.55 Aircraft.WingXMaxIt = 60 # # Maximum velocity for plotting purposes # Aircraft.VmaxPlt = 150 * FT / SEC # # Estimate for the time the aircraft rotates on the ground during takeoff # Aircraft.RotationTime = 0.1 * SEC