HTail.Airfoil = 'NACA0012' #HTail.AR = 3 HTail.b = 42 * IN HTail.TR = 1.0 HTail.o_eff = 0.96 HTail.S = 480 * IN**2 HTail.L = 45.5 * IN #Length from X_CG to Tail AC #HTail.VC = 0.70 # 0.8 for S1223 airfoil HTail.FullWing = True HTail.DWF = 1 #Main wing Down wash factor (Typically between 1.0 (close to wing) and 2.0 (far away)) HTail.Inverted = False HTail.ClSlopeAt = (-5 * ARCDEG, 10 * ARCDEG) HTail.CmSlopeAt = (-4 * ARCDEG, 5 * ARCDEG) Aircraft.HTailPos = 0 #T-Tail =1 regular tail =0 # # Elevator properties # HTail.Elevator.Fc = 0.5 #Elevator % of Tail chord HTail.Elevator.Fb = 1.0 #Elevator 100% of rear tail span HTail.Elevator.Ft = 0.0 #0.25 HTail.Elevator.Weight = 0.1 * LBF HTail.Elevator.WeightGroup = "HTail" HTail.Elevator.Servo.Fc = 0.3 HTail.Elevator.Servo.Fbc = 0.15 #Relocating the HTail Servo closer to the elevator HTail.Elevator.Servo.Weight = 0.3 * OZF HTail.Elevator.Servo.WeightGroup = "Controls" HTail.Elevator.Servo.Torque = 33.3 * IN * OZM #Set the sweep about the elevator hinge HTail.SweepFc = 1.0 - HTail.Elevator.Fc #Makes Elevator LE straight
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) HTail.FullWing = True # Full wing surface (i.e. top and bottom tail) HTail.Inverted = True # Invert the airfoil section HTail.b = 48 * IN # horizontal tail span #MJZ was 50 in sholsinger #HTail.S = 590.4 * IN**2 # horizontal tail planform area was 600 in**2 sholsinger HTail.S = 650 * IN**2 # horizontal tail planform area was 650 in**2 sholsinger HTail.L = 40 * IN # horizontal tail "length", dist back from wing AC was 55 HTail.TR = 1.0 # horizontal tail taper ratio HTail.o_eff = 0.97 # horizontal tail oswald #MJZ HTail.SweepFc = 1.0 - HTail.Elevator.Fc # sweep bout hinge, (Elevator LE straight) HTail.DWF = 1 # Main wing Down wash factor (b/w 1 (close to wing), 2 (far away))