# # 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 # ############################################################################### #============================================================================== # Horizontal tail #
# 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 ############################################################################### # # Tail surfaces # ###############################################################################
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
#==============================================================================#
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)