[VERSION] major = 1 minor = 0 [WEIGHT_AND_BALANCE] max_gross_weight = 777000 ; empty_weight = 370000 ; Empty weight, (LBS) reference_datum_position = 0, 0, 0 ; (was 95.5,0,0) Position of reference datum relative to FS(0,0,0) (FEET), z, x, y empty_weight_CG_position = -10.55, 0, 1.29 ;-12.55, 0, 1.29;-10.55, 0, 1.29 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y CG_forward_limit = 0.14 ; Gravity center forward limit in %MAX (divided by 100: 0.14 = 14%MAC) CG_aft_limit = 0.44 ; Gravity center aft limit in %MAX (divided by 100: 0.44 = 44%MAC) empty_weight_pitch_MOI = 16194640; was 26751456 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET) empty_weight_roll_MOI = 8360376; was 8943070 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET) empty_weight_yaw_MOI = 15527946; was 30764175 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET) empty_weight_coupled_MOI = 0 ; Empty transverse moment of inertia, Jyz (SLUG SQ FEET) max_number_of_stations = 10 ; Typical amount of seats:365 ; based on B777-300ER SWISS (320) station_load.0 = 185, 96, -1.8, 1, TT:MENU.PAYLOAD.PILOT, 1 station_load.1 = 185, 96, 1.8, 1, TT:MENU.PAYLOAD.COPILOT, 2 station_load.2 = 1124, 80, 0, 1, TT:MENU.PAYLOAD.CREW, 0 ; 6 station_load.3 = 1345, 70.5, 0, 1, TT:MENU.PAYLOAD.FIRST_CLASS, 0 ; 8 station_load.4 = 11618, 23, 0, 1, TT:MENU.PAYLOAD.BUSINESS_CLASS, 0 ; 62 station_load.5 = 4498, -5, 0, 1, TT:MENU.PAYLOAD.PREMIUM_ECONOMY, 0 ; 24 station_load.6 = 18739, -25, 0, 1, TT:MENU.PAYLOAD.FORWARD_ECONOMY, 0 ; 100 station_load.7 = 23612, -70, 0, 1, TT:MENU.PAYLOAD.REAR_ECONOMY, 0 ; 126 station_load.8 = 16875, 54, 0, -5, TT:MENU.PAYLOAD.FORWARD_BAGGAGE, 6 station_load.9 = 12250, -60, 0, -5, TT:MENU.PAYLOAD.REAR_BAGGAGE, 6 [CONTACT_POINTS] static_pitch = -0.750 ; degrees, pitch when at rest on the ground (+=Up, -=Dn) static_cg_height = 13.234 ; feet, altitude of CG when at rest on the ground gear_system_type = 1 ; gear system type (betweeen 0 and 4) 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none, 5 = undefined tailwheel_lock = 0 ; Is tailwheel lock available TRUE/FALSE gear_locked_on_ground = 1 ; Defines whether or not the landing gear handle is locked to down when the plane is on the ground. gear_locked_above_speed = 260 ; Defines the speed at which the landing gear handle becomes locked in the up position. (-1 = Disabled) max_speed_full_steering = 28;300 ; Defines the speed under which the full angle of steering is available (in feet/second). max_speed_decreasing_steering = 60;350 ; Defines the speed above which the angle of steering stops decreasing (in feet/second). min_available_steering_angle_pct = 0.10 ; Defines the percentage of steering which will always be available even above max_speed_decreasing_steering (in percent over 100). max_speed_full_steering_castering = 28 ; Defines the speed under which the full angle of steering is available for free castering wheels (in feet/second). max_speed_decreasing_steering_castering = 60 ; Defines the speed above which the angle of steering stops decreasing for free castering wheels (in feet/second). min_castering_angle = 0.05236 ; Defines the minimum angle a free castering wheel can take (in radians). max_castering_angle = 0.87 ; Defines the maximum angle a free castering wheel can take (in radians). max_number_of_points = 13 ; Number of contact points point.0 = 1, 84.1, 0.0, -18.85, 720, 0, 1.8, 70, 1.3, 1.5, 0.6, 11, 11, 0, 270, 290, 2 point.1 = 1, -23.8, -18.0, -19.80, 1500, 1, 2.2, 6.5, 1.4, 1.5, 0.5, 12, 12, 2, 270, 290, 2 point.2 = 1, -23.8, 18.0, -19.80, 1500, 2, 2.2, 6.5, 1.4, 1.5, 0.5, 12, 12, 3, 270, 290, 2 point.3 = 2, -53.0, -100.2, 4.50, 100, 0, 0, 0, 0, 0, 0, 0, 0, 5, 0, 0, 1 point.4 = 2, -53.0, 100.2, 4.50, 100, 0, 0, 0, 0, 0, 0, 0, 0, 6, 0, 0, 1 point.5 = 2, 75.0, 0.0, -10.20, 100, 0, 0, 0, 0, 0, 0, 0, 0, 9, 0, 0, 1 point.6 = 2, -136.0, 0.0, 1.50, 720, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1 point.7 = 2, -137.0, 0.0, 40.00, 500, 0, 0, 0, 0, 0, 0, 0, 0, 8, 0, 0, 1 point.8 = 2, 103.5, 0.0, -2.00, 100, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1 point.9 = 2, -108.1, 0.0, -6.10, 720, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1 point.10= 2, 10.0, 0.0, -10.80, 100, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1 point.11= 2, 13.0, -32.3, -15.70, 720, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1 point.12= 2, 13.0, 32.3, -15.70, 720, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1 emergency_extension_type=1 hyd_need_power_to_function=0 steering_time_constants= 3, 5 [FUEL] LeftMain = -18.5,-49, 0, 10300, 0 ; For each tank: Tank position (z longitudinal, x lateral, y vertical) (FEET), total fuel capacity (GALLONS), unusable fuel capacity (GALLONS) RightMain = -18.5, 49, 0, 10300, 0 Center1 = -4.1, 0, -5, 27290, 0 Center2 = 0, 0, 0, 0, 0 Center3 = 0, 0, 0, 0, 0 LeftAux = 0, 0, 0, 0, 0 LeftTip = 0, 0, 0, 0, 0 RightAux = 0, 0, 0, 0, 0 RightTip = 0, 0, 0, 0, 0 External1 = 0, 0, 0, 0, 0 External2 = 0, 0, 0, 0, 0 fuel_type = 2 ; 1 = OCTANE 100, 2 = JET_A, 3 = OCTANE 80, 4 = AUTO GAS, 5 = JET B number_of_tank_selectors = 1 ; Max 4 electric_pump = 1 engine_driven_pump = 1 manual_transfer_pump = 0 manual_pump = 0 anemometer_pump = 0 fuel_dump_rate = 0.1 default_fuel_tank_selector.1 = 1 ; Default fuel selector used in case of autostart for engine 1, default is ALL. default_fuel_tank_selector.2 = 1 ; Default fuel selector used in case of autostart for engine 2, default is ALL. [FUEL_SYSTEM] APU.1 = Name:APU#FuelBurnRate:10 Engine.1 = Name:LeftEngine#Index:1 Engine.2 = Name:RightEngine#Index:2 Tank.1 = Name:CenterTank #Title:TT:MENU.FUEL.CENTER #Capacity:27290 #UnusableCapacity:0 #Position: -4.1, 0, -5 #Priority:1 #OutputOnlyLines:CenterTankToCenterPumpLeft,CenterTankToCenterPumpRight Tank.2 = Name:MainTank1 #Title:TT:MENU.FUEL.LEFT_MAIN #Capacity:10300 #UnusableCapacity:0 #Position: -18.5,-49, 0 #Priority:2 #OutputOnlyLines:MainTank1ToMainTank1PumpFwd,MainTank1ToMainTank1PumpAft Tank.3 = Name:MainTank2 #Title:TT:MENU.FUEL.RIGHT_MAIN #Capacity:10300 #UnusableCapacity:0 #Position: -18.5, 49, 0 #Priority:2 #OutputOnlyLines:MainTank2ToMainTank2PumpFwd,MainTank2ToMainTank2PumpAft Line.1 = Name:CenterTankToCenterPumpLeft#Source:CenterTank#Destination:CenterTankPumpLeft Line.2 = Name:CenterTankToCenterPumpRight#Source:CenterTank#Destination:CenterTankPumpRight Line.3 = Name:CenterPumpLToCenterLeftJunc#Source:CenterTankPumpLeft#Destination:CenterLeftJunction Line.4 = Name:CenterPumpRToCenterRightJunc#Source:CenterTankPumpRight#Destination:CenterRightJunction Line.5 = Name:MainTank1ToMainTank1PumpFwd#Source:MainTank1#Destination:MainTank1PumpFwd Line.6 = Name:MainTank1ToMainTank1PumpAft#Source:MainTank1#Destination:MainTank1PumpAft Line.7 = Name:MainTank1PumpFwdToMainTank1Junc#Source:MainTank1PumpFwd#Destination:MainTank1Junction Line.8 = Name:MainTank1PumpAftToMainTank1Junc#Source:MainTank1PumpAft#Destination:MainTank1Junction Line.9 = Name:MainTank1JuncToEng1Junc#Source:MainTank1Junction#Destination:Eng1Junction Line.10 = Name:Eng1JuncToEng1Pump#Source:Eng1Junction#Destination:Eng1Pump Line.11 = Name:LeftEngineValveToLeftEngine#Source:LeftEngineValve#Destination:LeftEngine Line.12 = Name:Eng1JuncToEng1XFeedValve#Source:Eng1Junction#Destination:LeftCrossFeedValve Line.13 = Name:Eng1XFeedValveToLeftSideJunc#Source:LeftCrossFeedValve#Destination:LeftSideJunction Line.14 = Name:MainTank1PumpFwdToMainTank1ToAPUJunc#Source:MainTank1PumpFwd#Destination:MainTank1ToAPUJunction Line.15 = Name:MainTank1ToAPUJuncToMainTank1Junc#Source:MainTank1ToAPUJunction#Destination:MainTank1Junction Line.16 = Name:MainTank1ToAPUJuncToMainTank1FwdToAPUJunc#Source:MainTank1ToAPUJunction#Destination:MainTank1FwdToAPUJunction Line.17 = Name:MainTank1ToAPUDCPump#Source:MainTank1#Destination:APUDCPump Line.18 = Name:APUDCPumpToMainTank1FwdToAPUJunction#Source:APUDCPump#Destination:MainTank1FwdToAPUJunction Line.19 = Name:MainTank1FwdToAPUValve#Source:MainTank1FwdToAPUJunction#Destination:APUValve Line.20 = Name:APUValveToAPU#Source:APUValve#Destination:APU Line.21 = Name:LeftSideJuncToCenterLeftJunc#Source:Eng1Junction#Destination:CenterLeftJunction Line.22 = Name:RightSideJuncToCenterRightJunc#Source:Eng2Junction#Destination:CenterRightJunction Line.23 = Name:CenterLeftJuncToCenterRightJunc#Source:CenterLeftJunction#Destination:CenterRightJunction Line.24 = Name:MainTank2ToMainTank2PumpFwd#Source:MainTank2#Destination:MainTank2PumpFwd Line.25 = Name:MainTank2ToMainTank2PumpAft#Source:MainTank2#Destination:MainTank2PumpAft Line.26 = Name:MainTank2PumpFwdToMainTank2Junc#Source:MainTank2PumpFwd#Destination:MainTank2Junction Line.27 = Name:MainTank2PumpAftToMainTank2Junc#Source:MainTank2PumpAft#Destination:MainTank2Junction Line.28 = Name:MainTank2JuncToEng2Junc#Source:MainTank2Junction#Destination:Eng2Junction Line.29 = Name:Eng2JuncToEng2Pump#Source:Eng2Junction#Destination:Eng2Pump Line.30 = Name:RightEngineValveToRightEngine#Source:RightEngineValve#Destination:RightEngine Line.31 = Name:Eng2JuncToEng2XFeedValve#Source:Eng2Junction#Destination:RightCrossFeedValve Line.32 = Name:Eng2XFeedValveToRightSideJunc#Source:RightCrossFeedValve#Destination:RightSideJunction Line.33 = Name:CenterLeftAftJetissonValveToMainJettisonJunc#Source:CenterLeftAftJetissonValve#Destination:MainJettisonJunction Line.34 = Name:CenterRightAftJetissonValveToMainJettisonJunc#Source:CenterRightAftJetissonValve#Destination:MainJettisonJunction Line.35 = Name:MainJettisonJuncToJetissonNozzleValve1#Source:MainJettisonJunction#Destination:JetissonNozzleValve1 Line.36 = Name:MainJettisonJuncToJetissonNozzleValve2#Source:MainJettisonJunction#Destination:JetissonNozzleValve2 Line.37 = Name:Eng1PumpToEng1Valve#Source:Eng1Pump#Destination:LeftEngineValve Line.38 = Name:Eng2PumpToEng2Valve#Source:Eng2Pump#Destination:RightEngineValve Junction.1 = Name:MainTank1Junction#InputOnlyLines:MainTank1PumpFwdToMainTank1Junc,MainTank1PumpAftToMainTank1Junc#OutputOnlyLines:MainTank1JuncToEng1Junc Junction.2 = Name:Eng1Junction#InputOnlyLines:MainTank1JuncToEng1Junc#OutputOnlyLines:Eng1JuncToEng1Pump Junction.3 = Name:MainTank2Junction#InputOnlyLines:MainTank2PumpFwdToMainTank2Junc,MainTank2PumpAftToMainTank2Junc#OutputOnlyLines:MainTank2JuncToEng2Junc Junction.4 = Name:Eng2Junction#InputOnlyLines:MainTank2JuncToEng2Junc#OutputOnlyLines:Eng2JuncToEng2Pump Junction.5 = Name:LeftSideJunction#InputOnlyLines:MainTank1Junction Junction.6 = Name:RightSideJunction#InputOnlyLines:MainTank2Junction Junction.7 = Name:CenterLeftJunction#InputOnlyLines:CenterPumpLToCenterLeftJunc Junction.8 = Name:CenterRightJunction#InputOnlyLines:CenterPumpRToCenterRightJunc Junction.9 = Name:MainTank1ToAPUJunction#OutputOnlyLines:MainTank1ToAPUJuncToMainTank1Junc,MainTank1ToAPUJuncToMainTank1FwdToAPUJunc Junction.10 = Name:MainTank1FwdToAPUJunction#InputOnlyLines:MainTank1ToAPUJuncToMainTank1FwdToAPUJunc,APUDCPumpToMainTank1FwdToAPUJunction Junction.11 = Name:MainJettisonJunction Valve.1 = Name:LeftCrossFeedValve#Circuit:1 Valve.2 = Name:RightCrossFeedValve#Circuit:2 Valve.3 = Name:LeftEngineValve#Circuit:3 Valve.4 = Name:RightEngineValve#Circuit:4 Valve.5 = Name:APUValve#Circuit:5 Valve.6 = Name:CenterLeftAftJetissonValve#Circuit:6 Valve.7 = Name:CenterRightAftJetissonValve#Circuit:7 Valve.8 = Name:JetissonNozzleValve1#Circuit:8 Valve.9 = Name:JetissonNozzleValve2#Circuit:9 Pump.1 = Name:CenterTankPumpLeft#Pressure:45#DestinationLine:CenterPumpLToCenterLeftJunc#TankFuelRequired:CenterTank#Type:Electric#Index:5 Pump.2 = Name:CenterTankPumpRight#Pressure:45#DestinationLine:CenterPumpRToCenterRightJunc#TankFuelRequired:CenterTank#Type:Electric#Index:6 Pump.3 = Name:MainTank1PumpFwd#Pressure:20#DestinationLine:MainTank1PumpFwdToMainTank1Junc#TankFuelRequired:MainTank1#Type:Electric#Index:1 Pump.4 = Name:MainTank1PumpAft#Pressure:20#DestinationLine:MainTank1PumpAftToMainTank1Junc#TankFuelRequired:MainTank1#Type:Electric#Index:2 Pump.5 = Name:MainTank2PumpFwd#Pressure:20#DestinationLine:MainTank2PumpFwdToMainTank2Junc#TankFuelRequired:MainTank2#Type:Electric#Index:3 Pump.6 = Name:MainTank2PumpAft#Pressure:20#DestinationLine:MainTank2PumpAftToMainTank2Junc#TankFuelRequired:MainTank2#Type:Electric#Index:4 Pump.7 = Name:APUDCPump#Pressure:10#DestinationLine:APUDCPumpToMainTank1FwdToAPUJunction#TankFuelRequired:MainTank1#Type:Electric#Index:7 Pump.8 = Name:Eng1Pump#Pressure:10#DestinationLine:Eng1PumpToEng1Valve#Type:EngineDriven#Index:1 Pump.9 = Name:Eng2Pump#Pressure:10#DestinationLine:Eng2PumpToEng2Valve#Type:EngineDriven#Index:2 Trigger.1 = Condition:Autostart_Enabled#EffectTrue:OpenValve.LeftEngineValve,OpenValve.RightEngineValve,OpenValve.LeftCrossFeedValve,OpenValve.RightCrossFeedValve,StartPump.CenterTankPumpLeft,StartPump.CenterTankPumpRight,StartPump.MainTank1PumpFwd,StartPump.MainTank1PumpAft,StartPump.MainTank2PumpFwd,StartPump.MainTank2PumpAft,StartPump.Eng1Pump,StartPump.Eng2Pump Trigger.2 = Condition:Autoshutdown_Enabled#EffectTrue:CloseValve.LeftEngineValve,CloseValve.RightEngineValve,CloseValve.RightCrossFeedValve,StopPump.CenterTankPumpLeft,StopPump.CenterTankPumpRight,StopPump.MainTank1PumpFwd,StopPump.MainTank1PumpAft,StopPump.MainTank2PumpFwd,StopPump.MainTank2PumpAft [AIRPLANE_GEOMETRY] wing_area = 4702 ; Wing area S (SQUARE FEET) wing_span = 212.6 ; Wing span b (FEET) wing_root_chord = 50.2 ; Wing root chord croot (FEET) wing_camber = 1 ; (DEGREES) wing_thickness_ratio = 0.03 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord wing_dihedral = 6.25 ; Dihedral angle Lambda (DEGREES) wing_incidence = 0 ; 2 ; 5 ; Wing incidence (DEGREES) wing_twist = -1.8 ; Wing twist epsilon (DEGREES) oswald_efficiency_factor = 0.765 ; Wing Oswald efficiency factor e (non dimensional) wing_winglets_flag = 0 ; Has winglets true/false wing_sweep = 32 ; Wing sweep (DEGREES) wing_pos_apex_lon = -2 ; Longitudinal (z) position of wing apex w.r.t reference datum (FEET) wing_pos_apex_vert = -5.5 ; Vertical (y) position of wing apex w.r.t reference datum (FEET) htail_area = 1089.954 ; Horizontal tail area (SQUARE FEET) htail_span = 70.630 ; Horizontal tail span (FEET) htail_pos_lon = -122.721 ; Longitudinal (z) position of horizontal tail w.r.t reference datum (FEET) htail_pos_vert = 4.841 ; 3 ; Vertical (y) position of horizontal tail w.r.t reference datum (FEET) htail_incidence = 0 ; 2 ;2.50 ;2.75 ; Horizontal tail incidence (DEGREES) htail_sweep = 35 ; Horizontal tail sweep angle (DEGREES) htail_thickness_ratio = 0.030 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord vtail_area = 573.178 ; Vertical tail area (SQUARE FEET) vtail_span = 30.315 ; Vertical tail span (FEET) vtail_sweep = 44 ; Vertical tail sweep angle (DEGREES) vtail_pos_lon = -109.569 ; Longitudinal (z) position of vertical tail w.r.t reference datum (FEET) vtail_pos_vert = 25.842 ; Vertical (y) position of vertical tail w.r.t reference datum (FEET) vtail_thickness_ratio = 0.04 ; Local thickness is local_chord(x)*vtail_thickness_ratio, x = lateral coord fuselage_length = 242 ; Nose to tail (FEET) fuselage_diameter = 22 fuselage_center_pos = -3, 0, 0 elevator_area = 274.30 ;194.554 ; Elevator area (SQUARE FEET) aileron_area = 76.50 ;50.852 ; Elevator area (SQUARE FEET) rudder_area = 195.50 ; 237.615 ; Elevator area (SQUARE FEET) elevator_up_limit = 30 ; Elevator max deflection up angle (DEGREES) elevator_down_limit = 25 ; Elevator max deflection down angle (absolute value) (DEGREES) aileron_up_limit = 30 ; Aileron max deflection angle (DEGREES) aileron_down_limit = 10 ; Aileron max deflection down angle (absolute value) (DEGREES) rudder_limit = 27 ; Rudder max deflection angle (absolute value) (DEGREES) rudder_trim_limit = 10 ; Rudder trim max deflection angle (absolute value) (DEGREES) elevator_trim_limit = 16 ; Elevator trim max angle (absolute value) (DEGREES) spoiler_limit = 60 ; Spoiler max deflection angle (absolute value) (DEGREES) aileron_span_outboard = 0.7 spoilerons_available = 1 ; Aircraft has spoilerons true/false aileron_to_spoileron_gain = 3 ; Aileron influence on spoileron angle (non-dimensional) min_ailerons_for_spoilerons = 10 ; Minimum aileron deflection (absolute value) in which spoilerons are active (DEGREES) min_flaps_for_spoilerons = 0 ; Minimum flaps deflection (absolute value) in which spoilerons are active (DEGREES) spoiler_extension_time = 2 ; Spoilers extension time (SECONDS) spoiler_handle_available = 1 ; Spoiler handles available true/false auto_spoiler_available = 1 ; Auto spoilers available true/false auto_spoiler_min_speed = 80 ; Auto spoilers minimum trigger speed auto_spoiler_auto_retracts = 1 positive_g_limit_flaps_up = 2.5 ; Flap positive load limit when up. Same dimension as gravity vector FEET/SECONDS^2 positive_g_limit_flaps_down = 2.0 ; Flap positive load limit when down. Same dimension as gravity vector FEET/SECONDS^2 negative_g_limit_flaps_up = -1.0 ; Flap negative load limit when up. Same dimension as gravity vector FEET/SECONDS^2 negative_g_limit_flaps_down = -1.0 ; Flap negative load limit when down. Same dimension as gravity vector FEET/SECONDS^2 load_safety_factor = 1.5 ; Flap negative load limit when down. Same dimension as gravity vector FEET/SECONDS^2 elevator_trim_neutral = 0 ; Elevator trim max angle (absolute value) (DEGREES), for indicators only (no influence on flight model) aileron_to_rudder_scale = 0 ; non-dimensional flap_to_aileron_scale = 0 ; non-dimensional aileron_to_elevator_gain = 0 fly_by_wire = 0 fly_by_wire_from_flaps = 0 elevator_elasticity_table =0.000000:1.000000, 600.000000:0.300000 aileron_elasticity_table =0.000000:1.000000, 600.000000:0.500000 rudder_elasticity_table =0.000000:1.000000, 600.000000:0.200000 elevator_trim_elasticity_table =0.000000:1.000000, 600.000000:0.300000 ;controls_reactivity_scalar = 0.8 load_g_limiter_g = 3.5 air_spoiler_limit=60 spoiler_disabled_by_flaps=0 [AERODYNAMICS] lift_coef_pitch_rate = -8.49511 lift_coef_daoa = 5.1; 2.19580 lift_coef_delta_elevator = -0.35839 lift_coef_horizontal_incidence = 1.89160 lift_coef_flaps = 1.5165 ; based on Aircraft Drag Polar Estimation Based on a Stochastic Hierarchical Model lift_coef_spoilers = -0.1 lift_coef_air_spoilers = -0.1 drag_coef_zero_lift = 0.024 ; 0.028 ; 0.013 ; 0.016; 0.0199; 0.0220; 0.0185; 0.02197; 0.024; (777-200LR paper) drag_coef_flaps = 0.156;0.14892 ; based on Aircraft Drag Polar Estimation Based on a Stochastic Hierarchical Model drag_coef_gear = 0.016; based on Aircraft Drag Polar Estimation Based on a Stochastic Hierarchical Model drag_coef_spoilers = 0.025 ; 0.11230 ;0.154;0.11230 drag_coef_air_spoilers= 0.025 ; 0.11230;0.154;0.11230 side_force_slip_angle = -0.17333 ; based on Project OpenSky side_force_roll_rate = 0 ; not in use side_force_yaw_rate = 0 ; not in use side_force_delta_rudder = 0 ; not in use pitch_moment_horizontal_incidence = 0 ; not in use pitch_moment_delta_elevator = -5.58388 ; The change in pitch moment per change in elevator deflection pitch_moment_delta_trim = -5.58388 ; The change in pitch moment per change in trim pitch_moment_pitch_damping = 0 ; not in use pitch_moment_aoa_0 = 0 ; not in use pitch_moment_daoa = 0 ; not in use pitch_moment_flaps = 0 ; not in use pitch_moment_gear = 0 ; not in use pitch_moment_spoilers = 0 ; not in use pitch_moment_delta_elevator_propwash = 0 ; not in use pitch_moment_pitch_propwash = 0 ; not in use roll_moment_slip_angle = 0 ; not in use roll_moment_roll_damping = 0 ; not in use roll_moment_yaw_rate = 0 ; not in use roll_moment_spoilers = 0 ; not in use roll_moment_delta_aileron = 0 ; not in use roll_moment_delta_rudder = 0 ; not in use roll_moment_delta_aileron_trim_scalar = 0 ; not in use yaw_moment_slip_angle = 0 ; not in use yaw_moment_roll = 0 ; not in use yaw_moment_yaw_damping = 0 ; not in use yaw_moment_yaw_propwash = 0 ; not in use yaw_moment_delta_aileron = 0 ; not in use yaw_moment_delta_rudder = 0 ; not in use yaw_moment_delta_rudder_propwash = 0 ; not in use yaw_moment_delta_rudder_trim_scalar = 0 ; not in use compute_aero_center = 0 aero_center_lift = -10.55 ; -12.55 ;init to center aileron_up_drag_coef = 0.1 aileron_down_drag_coef = 0.05 elevator_lift_coef = 5.0 rudder_lift_coef = 5.0 lift_coef_aoa_table =-3.143:0,-0.800:-3.646,-0.035:0.162,-0.017:0.249,0.000:0.336,0.017:0.423,0.035:0.510,0.052:0.597,0.087:0.770,0.122:0.944,0.157:1.118,0.260:1.630,3.143:0 lift_coef_ground_effect_mach_table =0.054:1.12,0.1:1.075,0.2:1.03,0.3:1.021,0.4:1.017,0.5:1.015,0.6:1.012,0.7:1.011,0.8:1.01,0.9:1.01,1.0:1.01 lift_coef_mach_table =0.0:1.0,0.2:1.02,0.4:1.05,0.6:1.115,0.8:1.246,1.0:1.18,1.2:0.6721,1.4:0.434,1.6:0.2952,1.8:0.2357,2.0:0.1864,2.2:0.1568,2.4:0.1481,2.60:0.1373,2.8:0.1274,3.0:0.1274,3.2:0.3274 drag_coef_zero_lift_mach_tab =0.0:0.0,0.5:0.0,0.55:0.0,0.6:0.0,0.65:0.0,0.7:0.0,0.75:0.0,0.8:0.0,0.85:0.0,0.9:0.0,0.95:0.0,1.0:0.0,1.1:0.0,1.5:0.0 pitch_moment_aoa_table =-3.143:0.0,-0.8:-1.361,-0.4:-0.654,-0.2:-0.63,-0.1:-0.405,0.0:0.0,0.2:0.786,0.23:0.834,0.26:0.866,0.29:0.86,0.31:0.842,0.4:0.827,0.8:1.509,3.143:0.0 pitch_moment_delta_elevator_aoa_table =-180.0:-1.0,-40.0:0.191,-20.0:0.043,-14.0:0.692,-7.0:0.987,0.0:1.0,7.0:0.995,14.0:0.962,20.0:0.452,40.0:0.19,180.0:-1.0 pitch_moment_horizontal_incidence_aoa_table =0.0:0.0 pitch_moment_daoa_aoa_table = 0:1 pitch_moment_pitch_alpha_table = 0:1 roll_moment_slip_angle_aoa_table = 0:1 roll_moment_roll_rate_aoa_table = 0:1 roll_moment_delta_aileron_aoa_table = 0:1 roll_moment_slip_angle_mach_table = 0:0 roll_moment_yaw_rate_mach_table = 0:0 yaw_moment_yaw_rate_aoa_table = 0:1 elevator_scaling_table =-1.0:1.0, 0.0:0.5, 1.0:1.0 aileron_scaling_table =-1.0:1.0, 0.0:0.1, 1.0:1.0 rudder_scaling_table =-1.0:1.0, 0.0:0.4, 1.0:1.0 aileron_load_factor_effectiveness_table = 0:1 lift_coef_at_drag_zero = 0.1725; 0.5 ;0.63 ; 0 ;0.7 ; −0.167 was 0.1 Aircraft Preliminary Sizing with PreSTo lift_coef_at_drag_zero_flaps = 0.1475; 0.61 ;0.63 ; 0 ; 0.63 ; −0.167 was 0.1 Aircraft Preliminary Sizing with PreSTo fuselage_lateral_cx = 0.4 yaw_moment_aoa_table=0.0:0.0 roll_moment_aoa_table=0.0:0.0 lift_coef_delta_elevator_mach_table=0:0 lift_coef_daoa_mach_table=0:0 lift_coef_pitch_rate_mach_table=0.0:0.0 lift_coef_horizontal_incidence_mach_table=0:0 side_force_slip_angle_mach_table = 0:0 side_force_delta_rudder_mach_table = 0:0 side_force_yaw_rate_mach_table = 0:0 side_force_roll_rate_mach_table = 0:0 pitch_moment_delta_elevator_mach_table=0.0:0.0 pitch_moment_daoa_mach_table=0.0:0.0 pitch_moment_pitch_rate_mach_table=0.0:0.0 pitch_moment_horizontal_incidence_mach_table=0.0:0.0 roll_moment_delta_rudder_mach_table=0.0:0.0 roll_moment_delta_aileron_mach_table=0.0:0.0 roll_moment_roll_rate_mach_table=0.0:0.0 yaw_moment_slip_angle_aoa_table = 0:1 yaw_moment_delta_rudder_aoa_table = 0:1 yaw_moment_delta_aileron_mach_table = 0:0 yaw_moment_yaw_rate_mach_table = 0:0 yaw_moment_roll_rate_mach_table = 0:0 [FLIGHT_TUNING] modern_fm_only = 1; (true) forces use of modern flight model regardless of what user selected in MSFS options menu. 0 (false) allows use of user-selected flight model ;empty_cg_deviation_limit = 20 ; Maximum deviation of empty weight cg allowed in wegiht & balance UI menu (in feet) ;icing_scalar = 1 ; Scales effect of icing on lift and weight cruise_lift_scalar = 1.0 ; 1.104 ; based on Aircraft Preliminary Sizing with PreSTo paper parasite_drag_scalar = 1.0 ; induced_drag_scalar = 1.785 ; 1.75 ; 1.40 flap_induced_drag_scalar = 1.0 elevator_effectiveness = 1.0 elevator_maxangle_scalar = 1.0 aileron_effectiveness = 1.7 rudder_effectiveness = 1.0 rudder_maxangle_scalar = 1.0;0.6 pitch_stability = 0.125 ;1.5;0.15 roll_stability = 0.125 ;0.5;0.15 yaw_stability = 0.125 ;1.0;0.25 pitch_gyro_stability = 4 ; 2 roll_gyro_stability = 2 yaw_gyro_stability = 2 elevator_trim_effectiveness = 1.25 aileron_trim_effectiveness = 1.0 rudder_trim_effectiveness = 1.0 aileron_up_drag_scalar = 1.0 aileron_down_drag_scalar = 1.0 hi_alpha_on_roll = 0 hi_alpha_on_yaw = 0 p_factor_on_yaw = 1 torque_on_roll = 0 gyro_precession_on_roll = 1 gyro_precession_on_yaw = 1 engine_wash_on_roll = 0 rudder_engine_wash_on_roll = 1 wingflex_scalar = 0.8 wingflex_offset = 0 stall_coef_at_min_weight = 0.73 predicted_moi_density_scalar_fuselage = 1 predicted_moi_density_scalar_wings = 1 elevator_maxangle_scalar = 1 elevator_chordangle_scalar = -1 htail_maxangle_scalar = -1 disable_assistances = 0 rudder_chordangle_scalar = -1 vtail_maxangle_scalar = -1 gyro_precession_on_pitch = 1 [REFERENCE SPEEDS] full_flaps_stall_speed = 0 ; 113 ; Knots True (KTAS) flaps_up_stall_speed = 0 ; 175 ; Knots True (KTAS) cruise_speed = 482 ; Knots True (KTAS) cruise_mach = 0.84 max_mach = 0.89 max_indicated_speed = 500 ; Red line (KIAS) max_flaps_extended = 274.030126 normal_operating_speed = 360 airspeed_indicator_max = 562.5 rotation_speed_min = 132 ; Min speed required (Kts) climb_speed = 250 ; Climb speed (Kts) cruise_alt = 43100 ; (ft) takeoff_speed = 150 ; Takeoff Speed (Kts) spawn_cruise_altitude = 5000 ; Spawn Cruise Altitude (ft) spawn_descent_altitude = 500 ; Spawn Descent Altitude (ft) best_angle_climb_speed = 0 ; Best angle climb speed (Kts) approach_speed = 0 ; Approach speed (Kts) max_gear_extended = 270 ; (Kts) best_glide = 0 crossover_speed = 0 best_single_engine_rate_of_climb_speed = 0 minimum_control_speed = 0 fly_assistant_use_dynamic_speeds = 0 [INTERACTIVE POINTS] number_of_interactive_points = 17 interactive_point.0 =0.400000 , 81.976997 , -9.200000, -1.800000, 0 , 0.000000, 0.000000, -80.000000 , 52.000000, 8.000000, 52.000000, 8.000000, 0.000000, 0.000000 interactive_point.1 =0.400000 , -92.281006 , 9.000000, -1.700000, 0 , 0.000000, 0.000000, 102.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.2 =0.400000 , 47.387001, -10.000000, -1.800000, 2 , 0.000000, 0.000000, -90.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.3 =0.400000 , 47.387001, 10.000000, -1.800000, 2 , 0.000000, 0.000000, 90.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.4 =0.400000 , -33.400002, -10.000000, -1.800000, 2 , 0.000000, 0.000000, -90.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.5 =0.400000 , -33.400002 , 10.000000, -1.800000, 2 , 0.000000, 0.000000, 90.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.6 =0.400000 , -92.681 , -9.000000, -1.700000, 2 , 0.000000, 0.000000, -102.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.7 =0.400000 , -92.681 , 9.000000, -1.700000, 2 , 0.000000, 0.000000, 102.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.8 =0.400000 , -92.681 , -9.000000, -1.700000, 2 , 0.000000, 0.000000, -102.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.9 =0.400000 , -92.681 , 9.000000, -1.700000, 2 , 0.000000, 0.000000, 102.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.10 =0.400000 , 81.987 , -9.200000, -1.800000, 0 , 0.000000, 0.000000, -80.000000 , 52.000000, 8.000000, 52.000000, 8.000000, 0.000000, 0.000000 interactive_point.11 =0.400000 , 81.976997 , 9.200000, -1.800000, 0 , 0.000000, 0.000000, 80.000000 , 52.000000, 8.000000, 52.000000, 8.000000, 0.000000, 0.000000 interactive_point.12 =0.400000 , 64.787003 , 5.600000, -8.060000, 1 , 0.000000, 0.000000, 90.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.13 =0.400000 , -65.580994 , 5.600000, -8.060000, 1 , 0.000000, 0.000000, 90.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.14 =0.400000 , -4.500000 , -58.250000, -12.600000, 3 , 0.000000, 0.000000, -45.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.15 =0.330000 , 102.887001 , 10.800000, -10.500000, 4 , 0.000000, 0.000000, 45.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 interactive_point.16 =0.330000 , -19.099998 , 0.000000, -11.000000, 5 , 0.000000, 0.000000, 0.000000 , 0.000000, 0.000000, 0.000000, 0.000000, 0.000000, 0.000000 [STALL PROTECTION] stall_protection = 1; Alpha Protection off_limit = 10; Alpha below which the Alpha Protection can be disabled (If also below off_yoke_limit) off_yoke_limit = 5; Yoke position (in Pct) below which the Alpha Protection can be disabled (If also below off_limit) on_limit = 12; Alpha above which the Alpha Protection timer starts on_goal = 11; The alpha that the Alpha Protection will attempt to reach when triggered timer_trigger = 5.0; Duration (in Sec) the alpha must be above on_limit before the Alpha Protection is triggered [FLAPS.0] type = 1 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge system_type = 1 ; Flap system type 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none system_type_index = 90 span-outboard = 0.69 ; Outboard span area (added area) (percentage, non dimensional) extending-time = 54 ; 36 Flap extension time (SECONDS) damaging-speed = 285 ; Speed above which flap is damaged (Kts) blowout-speed = 350 ; Speed above which flap is blown out (Kts) maneuvering_flaps = 0 lift_scalar = 1.1 ; high-lift device Scalar coefficient to ponderate global flap lift coef (non dimensioned) drag_scalar = 0.9 ; high-lift device Scalar coefficient to ponderate global flap drag coef (non dimensioned) pitch_scalar = 0.95 ; high-lift device Scalar coefficient to ponderate global flap pitch coef (non dimensioned) max_on_ground_position = 6 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found. ;delay_between_flap_index = 1 flaps-position.0 = 0, -1, 0, 0, 0, 0, 0.22 ;flaps pos, airspeed limit, drag scalar, lift scalar, area sclar flaps-position.1 = 1, 255, 1.00, 1.00, 1, 0, 0.15 ; FLAPS 1 flaps-position.2 = 5, 235, 0.95, 1.05, 1, 0, 0.11 ; FLAPS 5 flaps-position.3 = 15, 215, 0.85, 1.10, 1, 0, 0.065 ; FLAPS 15 flaps-position.4 = 20, 195, 0.90, 1.05, 1, 0, -0.035 ; FLAPS 20 flaps-position.5 = 25, 185, 0.95, 0.95, 1, 0, -0.085 ; FLAPS 25 flaps-position.6 = 30, 170, 1.00, 0.75, 1, 0, -0.15 ; FLAPS 30 [FLAPS.1] type = 2 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge system_type = 1 ; Flap system type 0 = electrical, 1 = hydraulic, 2 = pneumatic, 3 = manual, 4 = none system_type_index = 89 span-outboard = 0.3 ; Outboard span area (added area) (percentage, non dimensional) extending-time = 43 ; Flap extension time (SECONDS) damaging-speed = 285 ; Speed above which flap is damaged (Kts) blowout-speed = 350 ; Speed above which flap is blown out (Kts) maneuvering_flaps = 0 lift_scalar = 1.0 ; high-lift device Scalar coefficient to ponderate global flap lift coef (non dimensioned) drag_scalar = 1.0 ; high-lift device Scalar coefficient to ponderate global flap drag coef (non dimensioned) pitch_scalar = 1.0 ; high-lift device Scalar coefficient to ponderate global flap pitch coef (non dimensioned) max_on_ground_position = 6 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found. ;delay_between_flap_index=0 flaps-position.0 = 0, -1, 0, 0 ; FLAPS UP flaps-position.1 = 10, 255, 0.10, 0.40 ; FLAPS 1 flaps-position.2 = 10, 235, 0.20, 0.55 ; FLAPS 5 flaps-position.3 = 10, 215, 0.40, 0.70 ; FLAPS 15 flaps-position.4 = 10, 195, 0.60, 0.85 ; FLAPS 20 flaps-position.5 = 20, 185, 0.80, 0.95 ; FLAPS 25 flaps-position.6 = 20, 170, 1.00, 1.00 ; FLAPS 30