# 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 ############################################################################### # # Tail surfaces #
# # 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