# Position the wing on the top of the fuselage # This does not to be changed at all since it is positioned correctly Aircraft.WingFuseFrac = 0.58 Aircraft.Wing.i = 0.0 * ARCDEG #Wing Incidence # Aircraft Properties #Total weight is going to change Aircraft.TotalWeight = 41.5 * LBF #52 to meet design criteria (190 & 100) #Engine Alignment Aircraft.EngineAlign = 0.75 Aircraft.TippingAngle = 10 * ARCDEG #Black Line on AC Plot Aircraft.RotationAngle = 8 * ARCDEG # Red line on AC plot Aircraft.Alpha_Groundroll = 0 * ARCDEG Aircraft.CMSlopeAt = (3 * ARCDEG, 12 * ARCDEG) Aircraft.CLSlopeAt = (3 * ARCDEG, 15 * ARCDEG) Aircraft.CLHTSlopeAt = (-5 * ARCDEG, 15 * ARCDEG) Aircraft.DWSlopeAt = (3 * ARCDEG, 15 * ARCDEG) Aircraft.Alpha_Zero_CM = 2 * ARCDEG #for steady level flight Aircraft.StaticMargin = 0.08 Aircraft.WingXMaxIt = 60 # # Maximum velocity for plotting purposes # Aircraft.VmaxPlt = 70 * FT / SEC # # Estimate for the time the aircraft rotates on the ground during takeoff # Aircraft.RotationTime = 0.1 * SEC
# # Position the wing on the bottom of the fuselage # Aircraft.WingFuseFrac = -0.30 # # Aircraft Properties # Aircraft.TotalWeight = 31 * LBF Aircraft.TippingAngle = 10 * ARCDEG Aircraft.RotationAngle = 10 * ARCDEG Aircraft.Alpha_Groundroll = 0 * ARCDEG Aircraft.CMSlopeAt = (10 * ARCDEG, 11 * ARCDEG) Aircraft.CLSlopeAt = (6 * ARCDEG, 7 * ARCDEG) Aircraft.CLHTSlopeAt = (8 * ARCDEG, 9 * ARCDEG) Aircraft.DWSlopeAt = (7 * ARCDEG, 8 * ARCDEG) Aircraft.Alpha_Zero_CM = 5 * ARCDEG Aircraft.StaticMargin = 0.1 # # Maximum velocity for plotting purposes # Aircraft.VmaxPlt = 70 * FT / SEC # # Estimate for the time the aircraft rotates on the ground during takeoff # Aircraft.RotationTime = 0.1 * SEC