[VERSION] major = 1 minor = 0 [WEIGHT_AND_BALANCE] max_gross_weight = 174165 ; Maximum takeoff weight, (LBS) empty_weight = 93697 ; Empty weight, (LBS); Includes weight to account for crew, pantry, galleys, lavs, potable water, emergency equipment etc. reference_datum_position = 0, 0, 0 ; Position of reference datum relative to FS(0,0,0) (FEET), z, x, y empty_weight_CG_position = -9.42, 0, 0 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y 30% CG CG_forward_limit = 0.16 ; Gravity center forward limit (longitudinal offset) for longitudinal stability CG_aft_limit = 0.4 ; Gravity center after limit (longitudinal offset z) w.r.t reference datum for longitudinal stability (FEET) empty_weight_pitch_MOI = 2453714 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET) empty_weight_roll_MOI = 989005 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET) empty_weight_yaw_MOI = 3166138 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET) empty_weight_coupled_MOI = 1000 ; Empty transverse moment of inertia, Jyz (SLUG SQ FEET) empty_inertia_tensor = 2453714, 3166138, 989005 activate_mach_limit_based_on_cg = 0 ; Activate mach limitation depending on CG position (true if > 0 /false othewise). Mostly for Concorde). activate_cg_limit_based_on_mach = 0 ; Activate cg limitation depending on mach value (true if > 0 /false othewise). Mostly for Concorde). ; weight & balance for A320-251N (WV055) - 174 economy class seats (Azul A20N) ; MRamp = 79400 kg/175047 lbs ; MTOW = 79000 kg/174165 lbs - should match line 1 above ; MLDW = 67400 kg/148591 lbs ; MZFW = 64300 kg/141757 lbs ; OEW = 42500 kg/93697 lbs ; Max Payload = 21800 kg/48060 lbs ; Max Fuel = 23721 ltrs (19046 kg)/6267 us gal (41989 lbs) @ specific gravity of 0.8 ISA conditions ; Average Adult pax assumed to be 185lbs/84kg ; Passenger baggage weight of 20 kg/pax is also added, making total pax + baggage weight = 104 kg/pax (i.e. Passenger weight on Simbrief) ; Starting load is 50% of capacity max_number_of_stations = 10 ; Number of payload stations station_load.0 = 3300, 20.5, 0, 5, ECONOMY ROWS 1-6 (seats: 36 max: 6670lbs/3024kg), 0 station_load.1 = 3850, 1.5, 0, 5.1, ECONOMY ROWS 7-13 (seats: 42 max: 7780lb/3530kg), 0 station_load.2 = 4400, -16.6, 0, 5.3, ECONOMY ROWS 14-21 (seats: 48 max: 8880lb/4032kg), 0 station_load.3 = 6600, -35.6, 0, 5.5, ECONOMY ROWS 22-29 (seats: 48 max: 8880lb/4032kg), 0 station_load.4 = 2800, 17.3, 0, 0.9, FWD BAGGAGE/CONTAINER (max: 7500lb/3402kg), 0 station_load.5 = 1950, -24.1, 0, 1, AFT CONTAINER (max: 5350lb/2426kg), 0 station_load.6 = 1700, -34.1, 0, 1.2, AFT BAGGAGE (max: 4650lb/2110kg), 0 station_load.7 = 1300, -42.4, 0, 1.4, AFT BULK/LOOSE (max: 3300lb/1497kg), 0 station_load.8 = 1, 40.7, 0, 0, PILOT, 1 station_load.9 = 1, 40.7, 0, 0, CO-PILOT, 2 [CONTACT_POINTS] static_pitch = -0.2 ; degrees, pitch when at rest on the ground (+=Up, -=Dn) static_cg_height = 8.89 ; feet, altitude of CG when at rest on the ground gear_system_type = 3 ; 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 max_number_of_points = 9 ; Number of contact points gear_locked_on_ground = 0 ; Defines whether or not the landing gear handle is locked to down when the plane is on the ground. gear_locked_above_speed = -1 ; Defines the speed at which the landing gear handle becomes locked in the up position. (-1 = Disabled)==> Disabled is kept in favor of an XML-based solution allow_stopped_steering = 1 ; This can be used to enable (TRUE, 1) steering when the aircraft is stopped or not (FALSE, 0). max_speed_full_steering = 300 ; Defines the speed under which the full angle of steering is available (in feet/second).==> 20 kts or 33.7 ft/sec (was 8) max_speed_decreasing_steering = 350 ; Defines the speed above which the angle of steering stops decreasing (in feet/second). ==> 40 kts or 67.5 ft/sec (was 50) min_available_steering_angle_pct = 0.0 ; Defines the percentage of steering which will always be available even above max_speed_decreasing_steering (in percent over 100) ===> 6 degrees or 0.08% of 75 degrees max deflection (was 0.2 or 15 degrees) max_speed_full_steering_castering = 300 ; Defines the speed under which the full angle of steering is available for free castering wheels (in feet/second). max_speed_decreasing_steering_castering = 350 ; 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 = 1.309 ; Defines the maximum angle a free castering wheel can take (in radians). ;CONTACT POINT DEFINITION ;0 Type of contact point - 1 = wheel, 2 = scrape point, 3 = skid, 4 = float, 5 = water rudder, 16 = ski, 17 = propeller ;1 Longitudinal position z relative to Datum Reference Point, in ft. ;2 Lateral position x relative to Datum Reference Point, in ft. ;3 Vertical position y relative to Datum Reference Point, in ft. ;4 Impact damage threshold crash velocity, in ft per minute. ;5 The brake type the wheel contact uses. - 1 = brake on left gear, 2 = brake on right gear, 3 = brake on both gears ;6 The wheel radius (including tire), in ft. ;7 Wheel max steering angle, in degrees, between -90 and 90. ;8 The static compression coefficient constant (which is used to compute spring reaction when on the ground), in ft. If the contact point is rigid, then set this to 0. ;9 The maximum static compression ratio. ;10 The damping ratio constant (used to compute ground reaction damping). A value between 0.0 (un-damped) and 1.0 (critically damped) ;11 Extension time, in seconds. This is the time required to fully extend wheels/water rudder/skis/floats. ;12 Retraction time, in seconds. This is the time required to fully retract wheels/water rudder/skis/floats. ;13 Identifies the type of sound that is going to be played for the contact point. 0 = Center Gear, 1 = Auxiliary Gear, 2 = Left Gear, 3 = Right Gear, 4 = Fuselage Scrape, 5 = Left Wing Scrape, 6 = Right Wing Scrape, 7 = Aux1 Scrape, 8 = Aux2 Scrape, 9 = Tail Scrape ;14 The airspeed limit for gears retraction, in kias. ;15 Airspeed above which gear is damaged, in kias. ;16 The exponential constant for springs ; 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 point.0 = 1, 27.44, 0, -9.55, 800, 0, 1.25, 95, 1.0, 1.88, 1.05, 10.6, 9.4, 0, 0, 0, 2.05 point.1 = 1, -14.03, -14, -9.83, 1200, 1, 1.9167, 0, 1.235, 1.39, 0.45, 11.1, 9.9, 2, 0, 0, 1.05 point.2 = 1, -14.03, 14, -9.83, 1200, 2, 1.9167, 0, 1.235, 1.39, 0.45, 11.1, 9.9, 3, 0, 0, 1.05 point.3 = 2, -26.00, -57, 6, 100, 0, 0, 0, 0, 0, 0, 0, 0, 5, 0, 0, 1 point.4 = 2, -26.00, 57, 6, 100, 0, 0, 0, 0, 0, 0, 0, 0, 6, 0, 0, 1 point.5 = 2, -79.20, 0, 8, 100, 0, 0, 0, 0, 0, 0, 0, 0, 9, 0, 0, 1 point.6 = 2, 44.07, 0, 2, 720, 0, 0, 0, 0, 0, 0, 0, 0, 4, 0, 0, 1 point.7 = 2, -68.00, 0, 4.1, 100, 0, 0, 0, 0, 0, 0, 0, 0, 7, 0, 0, 1 point.8 = 2, -75.20, 0, 32.3, 100, 0, 0, 0, 0, 0, 0, 0, 0, 8, 0, 0, 1 [FUEL] fuel_type = 2 ; 1 = OCTANE 100, 2 = JET_A, 3 = OCTANE 80, 4 = AUTO GAS, 5 = JET B [FUEL_SYSTEM] Version = 4 APU.1 = Name:APU#FuelBurnRate:33 Engine.1 = Name:LeftEngine#Index:1 Engine.2 = Name:RightEngine#Index:2 Tank.1 = Name:Center#Title:TT:MENU.FUEL.CENTER#Capacity:2179#UnusableCapacity:0#Position:-4.5,0,1#Priority:1#OutputOnlyLines:TankCenterToCenterTankJetPumpL,TankCenterToCenterTankJetPumpR Tank.2 = Name:LeftInner#Title:TT:MENU.FUEL.LEFT_INNER#Capacity:1816#UnusableCapacity:0#Position:-8,-13,2#Priority:2#InputOnlyLines:AutoCenterXferValveLToLeftInner,CenterXferJunctionLToLeftInner,LeftXferValve2ToLeftInnerTank#OutputOnlyLines:TankLeftInnerToLeftTankPump1,TankLeftInnerToLeftTankPump2 Tank.3 = Name:RightInner#Title:TT:MENU.FUEL.RIGHT_INNER#Capacity:1816#UnusableCapacity:0#Position:-8,13,2#Priority:2#InputOnlyLines:AutoCenterXferValveRToRightInner,CenterXferJunctionRToRightInner,RightXferValve2ToRightInnerTank#OutputOnlyLines:TankRightInnerToRightTankPump1,TankRightInnerToRightTankPump2 Tank.4 = Name:LeftOuter#Title:TT:MENU.FUEL.LEFT_OUTER#Capacity:228#UnusableCapacity:0#Position:-16.9,-27,3#Priority:3#OutputOnlyLines:LeftOuterTankToLeftXferValve1,LeftOuterTankToLeftXferValve2 Tank.5 = Name:RightOuter#Title:TT:MENU.FUEL.RIGHT_OUTER#Capacity:228#UnusableCapacity:0#Position:-16.9,27,3#Priority:3#OutputOnlyLines:RightOuterTankToRightXferValve1,RightOuterTankToRightXferValve2 Line.1 = Name:TankLeftInnerToLeftTankPump1#Source:LeftInner#Destination:LeftInnerTankPump1 Line.2 = Name:TankRightInnerToRightTankPump1#Source:RightInner#Destination:RightInnerTankPump1 Line.3 = Name:TankLeftInnerToLeftTankPump2#Source:LeftInner#Destination:LeftInnerTankPump2 Line.4 = Name:TankRightInnerToRightTankPump2#Source:RightInner#Destination:RightInnerTankPump2 Line.5 = Name:TankCenterToCenterTankJetPumpL#FuelFlowAt1PSI:0.00675#Source:Center#Destination:CenterTankJetPumpL Line.6 = Name:TankCenterToCenterTankJetPumpR#FuelFlowAt1PSI:0.00675#Source:Center#Destination:CenterTankJetPumpR Line.7 = Name:PumpLeft1ToJuncLeft#Source:LeftInnerTankPump1#Destination:LeftJunction Line.8 = Name:PumpRight1ToJuncRight#Source:RightInnerTankPump1#Destination:RightJunction Line.9 = Name:PumpLeft2ToJuncLeft#Source:LeftInnerTankPump2#Destination:LeftJunction Line.10 = Name:PumpRight2ToJuncRight#Source:RightInnerTankPump2#Destination:RightJunction Line.11 = Name:JuncLeftToEngValveLeft#Source:LeftJunction#Destination:LeftEngineValve Line.12 = Name:JuncRightToEngValveRight#Source:RightJunction#Destination:RightEngineValve Line.13 = Name:JuncLeftToJuncAPU#Source:LeftJunction#Destination:APUJunction Line.14 = Name:JuncAPUToCrossFeedValve#Source:APUJunction#Destination:CrossFeedValve Line.15 = Name:CrossFeedValveToJuncRight#Source:CrossFeedValve#Destination:RightJunction Line.16 = Name:JuncAPUToAPUPump#Source:APUJunction#Destination:APUPump Line.17 = Name:APUPumpToAPUValve#Source:APUPump#Destination:APUValve Line.18 = Name:APUValveToAPU#Source:APUValve#Destination:APU Line.19 = Name:EngValveLeftToEngLeft#Source:LeftEngineValve#Destination:LeftEngine Line.20 = Name:EngValveRightToEngRight#Source:RightEngineValve#Destination:RightEngine Line.21 = Name:CenterTankJetPumpLToCenterXferDisableValveL#FuelFlowAt1PSI:0.00675#Source:CenterTankJetPumpL#Destination:CenterTransferDisableValveL Line.22 = Name:CenterTankJetPumpRToCenterXferDisableValveR#FuelFlowAt1PSI:0.00675#Source:CenterTankJetPumpR#Destination:CenterTransferDisableValveR Line.23 = Name:CenterXferDisableValveLToCenterXferJunctionL#FuelFlowAt1PSI:0.00675#Source:CenterTransferDisableValveL#Destination:CenterTransferJunctionL Line.24 = Name:CenterXferDisableValveRToCenterXferJunctionR#FuelFlowAt1PSI:0.00675#Source:CenterTransferDisableValveR#Destination:CenterTransferJunctionR Line.25 = Name:CenterXferJunctionLToAutoCenterXferValveL#FuelFlowAt1PSI:0.00675#Source:CenterTransferJunctionL#Destination:AutoCenterTransferValveL Line.26 = Name:CenterXferJunctionRToAutoCenterXferValveR#FuelFlowAt1PSI:0.00675#Source:CenterTransferJunctionR#Destination:AutoCenterTransferValveR Line.27 = Name:CenterXferJunctionLToLeftInner#FuelFlowAt1PSI:0.00675#Source:CenterTransferJunctionL#Destination:LeftInner Line.28 = Name:CenterXferJunctionRToRightInner#FuelFlowAt1PSI:0.00675#Source:CenterTransferJunctionR#Destination:RightInner Line.29 = Name:AutoCenterXferValveLToLeftInner#FuelFlowAt1PSI:0.00675#Source:AutoCenterTransferValveL#Destination:LeftInner Line.30 = Name:AutoCenterXferValveRToRightInner#FuelFlowAt1PSI:0.00675#Source:AutoCenterTransferValveR#Destination:RightInner Line.31 = Name:LeftOuterTankToLeftXferValve1#Source:LeftOuter#Destination:LeftTransferValve1#GravityBasedFuelFlow:600 Line.32 = Name:RightOuterTankToRightXferValve1#Source:RightOuter#Destination:RightTransferValve1#GravityBasedFuelFlow:600 Line.33 = Name:LeftXferValve1ToLeftInnerTank#Source:LeftTransferValve1#Destination:LeftInner#GravityBasedFuelFlow:600 Line.34 = Name:RightXferValve1ToRightInnerTank#Source:RightTransferValve1#Destination:RightInner#GravityBasedFuelFlow:600 Line.35 = Name:LeftOuterTankToLeftXferValve2#Source:LeftOuter#Destination:LeftTransferValve2#GravityBasedFuelFlow:600 Line.36 = Name:RightOuterTankToRightXferValve2#Source:RightOuter#Destination:RightTransferValve2#GravityBasedFuelFlow:600 Line.37 = Name:LeftXferValve2ToLeftInnerTank#Source:LeftTransferValve2#Destination:LeftInner#GravityBasedFuelFlow:600 Line.38 = Name:RightXferValve2ToRightInnerTank#Source:RightTransferValve2#Destination:RightInner#GravityBasedFuelFlow:600 Junction.1 = Name:LeftJunction#InputOnlyLines:PumpLeft1ToJuncLeft,PumpLeft2ToJuncLeft#OutputOnlyLines:JuncLeftToEngValveLeft Junction.2 = Name:APUJunction#OutputOnlyLines:JuncAPUToAPUPump Junction.3 = Name:RightJunction#InputOnlyLines:PumpRight1ToJuncRight,PumpRight2ToJuncRight#OutputOnlyLines:JuncRightToEngValveRight Junction.4 = Name:CenterTransferJunctionL#InputOnlyLines:CenterXferDisableValveLToCenterXferJunctionL#OutputOnlyLines:CenterXferJunctionLToAutoCenterXferValveL,CenterXferJunctionLToLeftInner#Option:CenterXferJunctionLToAutoCenterXferValveL#Option:CenterXferJunctionLToLeftInner Junction.5 = Name:CenterTransferJunctionR#InputOnlyLines:CenterXferDisableValveRToCenterXferJunctionR#OutputOnlyLines:CenterXferJunctionRToAutoCenterXferValveR,CenterXferJunctionRToRightInner#Option:CenterXferJunctionRToAutoCenterXferValveR#Option:CenterXferJunctionRToRightInner Valve.1 = Name:LeftEngineValve#OpeningTime:1.7#Circuit:1 Valve.2 = Name:RightEngineValve#OpeningTime:1.7#Circuit:2 Valve.3 = Name:CrossFeedValve#OpeningTime:3#Circuit:3 Valve.4 = Name:LeftTransferValve2#Circuit:4 Valve.5 = Name:RightTransferValve2#Circuit:5 Valve.6 = Name:LeftTransferValve1#Circuit:6 Valve.7 = Name:RightTransferValve1#Circuit:7 Valve.8 = Name:APUValve#OpeningTime:3#Circuit:8 Valve.9 = Name:CenterTransferDisableValveL#DestinationLine:CenterXferDisableValveLToCenterXferJunctionL#Circuit:9 ; When overhead transfer button is OFF, this valve is closed and disables fuel flow in both manual and automatic modes Valve.10 = Name:CenterTransferDisableValveR#DestinationLine:CenterXferDisableValveRToCenterXferJunctionR#Circuit:10 ; When overhead transfer button is OFF, this valve is closed and disables fuel flow in both manual and automatic modes Valve.11 = Name:AutoCenterTransferValveL#DestinationLine:AutoCenterXferValveLToLeftInner#Circuit:11 Valve.12 = Name:AutoCenterTransferValveR#DestinationLine:AutoCenterXferValveRToRightInner#Circuit:12 Pump.1 = Name:CenterTankJetPumpL#Pressure:10#DestinationLine:CenterTankJetPumpLToCenterXferDisableValveL#TankFuelRequired:Center#Type:Electric#Index:1 Pump.2 = Name:LeftInnerTankPump1#Pressure:25#DestinationLine:PumpLeft1ToJuncLeft#TankFuelRequired:LeftInner#Type:Electric#Index:3 Pump.3 = Name:RightInnerTankPump1#Pressure:25#DestinationLine:PumpRight1ToJuncRight#TankFuelRequired:RightInner#Type:Electric#Index:4 Pump.4 = Name:CenterTankJetPumpR#Pressure:10#DestinationLine:CenterTankJetPumpRToCenterXferDisableValveR#TankFuelRequired:Center#Type:Electric#Index:2 Pump.5 = Name:LeftInnerTankPump2#Pressure:25#DestinationLine:PumpLeft2ToJuncLeft#TankFuelRequired:LeftInner#Type:Electric#Index:5 Pump.6 = Name:RightInnerTankPump2#Pressure:25#DestinationLine:PumpRight2ToJuncRight#TankFuelRequired:RightInner#Type:Electric#Index:6 Pump.7 = Name:APUPump#Pressure:15#DestinationLine:APUPumpToAPUValve#TankFuelRequired:LeftInner#Type:Electric#Index:7 Trigger.1 = Name:StartCenterTankXferToLeftInner#Target:LeftInner#Threshold:1651.5#Condition:TankQuantityBelow#EffectTrue:OpenValve.AutoCenterTransferValveL Trigger.2 = Name:StartCenterTankXferToRightInner#Target:RightInner#Threshold:1651.5#Condition:TankQuantityBelow#EffectTrue:OpenValve.AutoCenterTransferValveR Trigger.3 = Name:StopCenterTankXferToLeftInner#Target:LeftInner#Threshold:1815#Condition:TankQuantityAbove#EffectTrue:CloseValve.AutoCenterTransferValveL Trigger.4 = Name:StopCenterTankXferToRightInner#Target:RightInner#Threshold:1815#Condition:TankQuantityAbove#EffectTrue:CloseValve.AutoCenterTransferValveR Trigger.5 = Name:StartOuterXferLeftInnerTrigger#Target:LeftInner#Threshold:246.8#Condition:TankQuantityBelow#EffectTrue:OpenValve.LeftTransferValve1,OpenValve.LeftTransferValve2,OpenValve.RightTransferValve1,OpenValve.RightTransferValve2 Trigger.6 = Name:StartOuterXferRightInnerTrigger#Target:RightInner#Threshold:246.8#Condition:TankQuantityBelow#EffectTrue:OpenValve.LeftTransferValve1,OpenValve.LeftTransferValve2,OpenValve.RightTransferValve1,OpenValve.RightTransferValve2 Trigger.7 = Name:StopLeftOuterXferToLeftInner#Target:LeftOuter#Threshold:227.9#Condition:TankQuantityAbove#EffectTrue:CloseValve.LeftTransferValve1,CloseValve.LeftTransferValve2 Trigger.8 = Name:StopRightOuterXferToRightInner#Target:RightOuter#Threshold:227.9#Condition:TankQuantityAbove#EffectTrue:CloseValve.RightTransferValve1,CloseValve.RightTransferValve2 Trigger.9 = Name:CloseCenterTankValves5MinAfterLowFuelLevel#Target:Center#Threshold:42.8#Condition:TankQuantityBelow#DelayTrue:300#EffectTrue:CloseValve.AutoCenterTransferValveL,CloseValve.AutoCenterTransferValveR Trigger.10 = Name:CloseCenterTankValvesIfReopenedWithNoCenterTankFueL#Target:LeftInner#Threshold:1651#Condition:TankQuantityBelow#EffectTrue:CloseValve.AutoCenterTransferValveL,CloseValve.AutoCenterTransferValveR Trigger.11 = Name:CloseCenterTankValvesIfReopenedWithNoCenterTankFueR#Target:RightInner#Threshold:1651#Condition:TankQuantityBelow#EffectTrue:CloseValve.AutoCenterTransferValveL,CloseValve.AutoCenterTransferValveR [AIRPLANE_GEOMETRY] wing_area = 1317.47 ; Wing area S (SQUARE FEET) wing_span = 117.454 ; Wing span b (FEET) wing_root_chord = 19.9 ; Wing root chord croot (FEET) wing_camber = 1 ; (DEGREES) wing_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord wing_dihedral = 5.11 ; Dihedral angle Lambda (DEGREES) wing_incidence = 2 ; Wing incidence (DEGREES) wing_twist = -2 ; Wing twist epsilon (DEGREES) oswald_efficiency_factor = 0.700 ; Wing Oswald efficiency factor e (non dimensional) wing_winglets_flag = 1 ; Has winglets true/false (not currently used by MSFS) wing_sweep = 25 ; Wing sweep (DEGREES) ;wing_pos_apex_lon = 0 ; Longitudinal (z) position of wing apex w.r.t reference datum (FEET) wing_pos_apex_vert = 0 ; Vertical (y) position of wing apex w.r.t reference datum (FEET) htail_area = 333.7 ; Horizontal tail area (SQUARE FEET) htail_span = 40.85 ; Horizontal tail span (FEET) htail_pos_lon = -68.3 ; Longitudinal (z) position of horizontal tail w.r.t reference datum (FEET) htail_pos_vert = 9 ; Vertical (y) position of horizontal tail w.r.t reference datum (FEET) htail_incidence = 0 ; Horizontal tail incidence (DEGREES) htail_sweep = 29 ; Horizontal tail sweep angle (DEGREES) htail_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord vtail_area = 231.5 ; Vertical tail area (SQUARE FEET) vtail_span = 19.26 ; Vertical tail span (FEET) vtail_sweep = 34 ; Vertical tail sweep angle (DEGREES) vtail_pos_lon = -65 ; Longitudinal (z) position of vertical tail w.r.t reference datum (FEET) vtail_pos_vert = 19.5 ; Vertical (y) position of vertical tail w.r.t reference datum (FEET) vtail_thickness_ratio = 0.03 ; Local thickness is local_chord(x)*vtail_thickness_ratio, x = lateral coord fuselage_length = 123.27 ; Nose to tail (FEET) fuselage_diameter = 13 fuselage_center_pos = -5, 0, 5 elevator_area = 96.6 ; Elevator area (SQUARE FEET) aileron_area = 31 ; Aileron area (SQUARE FEET) rudder_area = 56.6 ; Rudder area (SQUARE FEET) elevator_up_limit = 25 ; Elevator max deflection up angle (DEGREES) Real value is 30 elevator_down_limit = 17 ; Elevator max deflection down angle (absolute value) (DEGREES) aileron_up_limit = 25 ; Aileron max deflection angle (DEGREES) aileron_down_limit = 25 ; Aileron max deflection down angle (absolute value) (DEGREES) rudder_limit = 25 ; Rudder max deflection angle (absolute value) (DEGREES) rudder_trim_limit = 0 ; Rudder trim max deflection angle (absolute value) (DEGREES) elevator_trim_up_limit = 13.5 ; Elevator trim max angle nose up direction (absolute value) (DEGREES) elevator_trim_down_limit = 4 ; Elevator trim max angle nose down direction (absolute value) (DEGREES) spoiler_limit = 50 ; Spoiler max deflection angle when on the ground (absolute value) (DEGREES) air_spoiler_limit = 40 ; Spoiler max deflection angle when in the air (absolute value) (DEGREES) spoilerons_available = 0 ; Aircraft has spoilerons true/false aileron_to_spoileron_gain = 0.5 ; Aileron influence on spoileron angle (non-dimensional) min_ailerons_for_spoilerons = 2 ; 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 = 0.1 ; Spoilers extension time (SECONDS), speed is now controlled by FBW spoiler_handle_available = 1 ; Spoiler handles available true/false auto_spoiler_available = 0 ; Auto spoilers available true/false auto_spoiler_min_speed = 72 ; Auto spoilers minimum trigger speed 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 = 0.0 ; Flap negative load limit when down. Same dimension as gravity vector FEET/SECONDS^2 load_safety_factor = 1.5 ; Safety factor applied to load limits. Unitless auto_spoiler_auto_retracts = 0 ; Auto spoilers retracts automatically true/false 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 fly_by_wire = 0 ; Fly-by-wire available true/false elevator_elasticity_table = 0:1, 400:1 aileron_elasticity_table = 0:1, 400:1 rudder_elasticity_table = 0:1, 400:1 elevator_trim_elasticity_table = 0:0.3, 58:0.75, 100:0.75, 120:1, 400:1 ;controls_reactivity_scalar = 1 ; Reactivity scalar for all controls [AERODYNAMICS] lift_coef_flaps = 1.867 ; Change in lift due to flaps lift_coef_spoilers = -0.466875 ; Change in lift due to spoilers drag_coef_zero_lift = 0.01865 ; The zero lift drag polar drag_coef_flaps = 0.1316 ; Change in drag due to flaps drag_coef_gear = 0.0372 ; Change in drag due to landing gear drag_coef_spoilers = 0.05775; Change in drag due to spoilers compute_aero_center = 0 aero_center_lift = -8.75 ; Init to center lift_coef_aoa_table = -3.15:0, 0:0.138, 0.139:1.32, 0.2:1.48, 0.26:1.76, 0.29:1.750, 0.32:1.60, 0.5:1.50, 3.15:0 lift_coef_ground_effect_mach_table = 0.0:1.178, 0.15:1.178, 0.19:1.178, 0.20:1.176, 0.22:1.173, 0.25:1.17, 0.27:1.1675, 0.30:1.164, 0.35:1.159, 1.0:1 drag_coef_zero_lift_mach_tab = 0:0, 0.5:0, 0.55:0, 0.6:0.0002, 0.65:0.0003, 0.7:0.0004, 0.75:0.0008, 0.8:0.0015, 0.85:0.010, 0.9:0.15, 0.95:0.333, 1:0.5 elevator_scaling_table = 0:1 ; scales control based on its deflection aileron_scaling_table = 0:1 ; scales control based on its deflection rudder_scaling_table = 0:1 ; scales control based on its deflection lift_coef_at_drag_zero = 0.1750 lift_coef_at_drag_zero_flaps = 0.4200 ;Legacy Aerodynamics Parameters (not used by modern flight model, but must be present) lift_coef_pitch_rate = -57.116 ; The change in lift per change in pitch rate lift_coef_daoa = 0 ; lift per change in angle of attack rate lift_coef_delta_elevator = -1.652 ; The change in lift per change in elevator deflection lift_coef_horizontal_incidence = 0 ; The change in lift per change in horizontal incidence angle side_force_slip_angle = -3.252 ; (yaw angle) The change in side force per change in side slip angle side_force_roll_rate = 1.833 ; (roll velocity) The change in side force per change in roll rate side_force_yaw_rate = 17.395 ; (yaw velocity) The change in side force per change in yaw rate side_force_delta_rudder = -2.793 ; The change in side force per change in rudder deflection pitch_moment_horizontal_incidence = 0 ; The change in pitch moment per change in horizontal incidence angle pitch_moment_delta_elevator = -11.780 ; The change in pitch moment per change in elevator deflection pitch_moment_delta_trim = -11.780 ; The change in pitch moment per change in trim pitch_moment_pitch_damping = -1245.917 ; The change in pitch moment per change in pitch rate(PRIMARY PITCH STABILITY FACTOR). deg/s pitch_moment_aoa_0 = -0.109 ; Pitch moment at zero angle - of - attack pitch_moment_daoa = 0 ; The change in pitch moment per change in angle of attack pitch_moment_flaps = -0.084 ; The pitch moment due to flaps pitch_moment_gear = 0.0022 ; The pitch moment due to gear pitch_moment_spoilers = 0.023 ; The pitch moment due to spoilers pitch_moment_delta_elevator_propwash = -11.780 pitch_moment_pitch_propwash = 0 roll_moment_slip_angle = 0.554 ; The change in roll moment per sideslip angle(DIHEDRAL EFFECT) roll_moment_roll_damping = -2.078 roll_moment_yaw_rate = -2.621 roll_moment_spoilers = 0 ; The change in roll moment due to spoilers roll_moment_delta_aileron = -0.291 ; (control)The change in roll moment per change in aileron deflection roll_moment_delta_rudder = 0.476 ; (control)The change in roll moment per change rudder deflection roll_moment_delta_aileron_trim_scalar = -0.291 ; Change in roll moment due to aileron trim yaw_moment_slip_angle = 1.296 ; The change in yaw moment per change sideslip angle(WEATHER VANING EFFECT) yaw_moment_roll = 0.742 ; (adverse yaw) The change in yaw moment per change in roll rate deg/s yaw_moment_yaw_damping = -67.303 ; (damping)The change in yaw moment per change in yaw rate(PRIMARY YAW STABILITY FACTOR deg/s) yaw_moment_yaw_propwash = 0 ; (damping) yaw_moment_delta_aileron = -0.007 ; (adverse yaw) The change in yaw moment per change aileron deflection yaw_moment_delta_rudder = 1.321 ; (control)The change in yaw moment per change in rudder deflection PRIMARY YAW POWER FACTOR yaw_moment_delta_rudder_propwash = 1.321 ; (control) yaw_moment_delta_rudder_trim_scalar = 1.321 ; Change in yaw moment due to rudder trim lift_coef_mach_table = 0:1 lift_coef_delta_elevator_mach_table = 0:0 lift_coef_daoa_mach_table = 0:0 lift_coef_pitch_rate_mach_table = 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_aoa_table = -3.15:0, -0.8:-2.402, -0.4:-1.861, -0.2:-0.842, -0.1:-0.442, 0:0, 0.2:1.173, 0.23:1.337, 0.26:1.489, 0.29:1.723, 0.31:1.919, 0.4:2.276, 0.8:2.992, 3.15:0 pitch_moment_delta_elevator_aoa_table = -180:-1, -40:0.05, -20:0.455, -10:0.853, -5:1.007, 0:1, 5:0.839, 10:0.693, 20:0.381, 40:-0.08, 180:-1; AoA(alpha) is given in DEGREES pitch_moment_horizontal_incidence_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES pitch_moment_daoa_aoa_table = 0:1 ; AoA(alpha) is given in DEGREES pitch_moment_pitch_alpha_table = 0:1 ; AoA(alpha) is given in DEGREES pitch_moment_delta_elevator_mach_table = 0:0 pitch_moment_daoa_mach_table = 0:0 pitch_moment_pitch_rate_mach_table = 0:0 pitch_moment_horizontal_incidence_mach_table = 0:0 pitch_moment_aoa_0_mach_table = 0:0 roll_moment_aoa_table = 0:0 ; Cl (roll moment coef) versus AoA 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_delta_rudder_mach_table = 0:0 roll_moment_delta_aileron_mach_table = 0:0 roll_moment_yaw_rate_mach_table = 0:0 roll_moment_roll_rate_mach_table = 0:0 yaw_moment_aoa_table = 0:0 ; Cn (yaw moment coef) versus AoA yaw_moment_slip_angle_aoa_table = 0:1 yaw_moment_yaw_rate_aoa_table = 0:1 yaw_moment_delta_rudder_aoa_table = 0:1 yaw_moment_slip_angle_mach_table = 0:0 yaw_moment_delta_rudder_mach_table = 0:0 yaw_moment_delta_aileron_mach_table = 0:0 yaw_moment_yaw_rate_mach_table = 0:0 yaw_moment_roll_rate_mach_table = 0:0 aileron_load_factor_effectiveness_table = 0:1 ; scaling of roll_moment_delta_aileron versus gravity forces, G effects on aileron effectiveness, acts on roll_moment_delta_aileron [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 disable_assistances = 0; 1(true) disables all AI assistance settings as they are not compatible with the addon cruise_lift_scalar = 0.93 parasite_drag_scalar = 1 induced_drag_scalar = 1.715 flap_induced_drag_scalar = 0.365 elevator_effectiveness = 1 elevator_maxangle_scalar = 0.465 aileron_effectiveness = 0.95 rudder_effectiveness = 0.21 rudder_maxangle_scalar = 0.97 pitch_stability = 4 roll_stability = 0.65 yaw_stability = 1 pitch_gyro_stability = 6 roll_gyro_stability = 4.5 yaw_gyro_stability = 1 elevator_trim_effectiveness = 3.89 aileron_trim_effectiveness = 1 rudder_trim_effectiveness = 0 p_factor_on_yaw = 0 torque_on_roll = 0 gyro_precession_on_roll = 0 gyro_precession_on_yaw = 0 engine_wash_on_roll = 0 ; Torque effect wingflex_scalar = 0.75 wingflex_offset = -0.25 ground_crosswind_effect_zero_speed = 10 ground_crosswind_effect_max_speed = 90 ground_high_speed_steeringwheel_static_friction_scalar = 1 ground_high_speed_otherwheel_static_friction_scalar = 1 ; Legacy Flight Tuning parameters hi_alpha_on_roll = 0 hi_alpha_on_yaw = 0 [REFERENCE SPEEDS] full_flaps_stall_speed = 115 ; Knots True (KTAS) flaps_up_stall_speed = 171 ; Knots True (KTAS) cruise_speed = 455 ; Knots True (KTAS) cruise_mach = 0.78 crossover_speed = 320 ; Knots Indicated (KIAS) max_mach = 0.82 ; MMO max_indicated_speed = 500 ; Red line (KIAS) max_flaps_extended = 274.030126 normal_operating_speed = 350 ; VMO airspeed_indicator_max = 562.5 rotation_speed_min = 120 ; Min speed required (Kts) climb_speed = 231 ; Climb speed (Kts) cruise_alt = 36000 ; (ft) takeoff_speed = 115 ; 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) best_glide = 0 ; Best Glide (Kts) max_gear_extended = 280 ; (Kts) [INTERACTIVE POINTS] number_of_interactive_points = 10 interactive_point.0 = 0.4, 27.93, -6.05, 3.02, 0, 0, 0, -86, 72, 16, 85, 3, -2, 33 interactive_point.1 = 0.4, 27.93, 6.05, 3.02, 0, 0, 0, 86, 85, 3, 72, 16, -2, 33 interactive_point.2 = 0.4, -53, -5.2, 3, 0, 0, 0, -103, 0, 0, 0, 0, 0, 0 interactive_point.3 = 0.4, -53, 5.2, 3, 0, 0, 0, 103, 0, 0, 0, 0, 0, 0 interactive_point.4 = 0.4, -29.5, 2, -1.8, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0 interactive_point.5 = 0.4, 18, 1.93, -1.9, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0 interactive_point.6 = 0.4, -4, -6, 6.2, 2, 0, 0, -90, 0, 0, 0, 0, 0, 0 interactive_point.7 = 0.4, -4, 6, 6.2, 2, 0, 0, 90, 0, 0, 0, 0, 0, 0 interactive_point.8 = 0, 36.3, 10.78, -5.18, 4, 0, 0, 45, 0, 0, 0, 0, 0, 0 interactive_point.9 = 0, 0, -54.59, -7.57, 3, 0, 0, -90, 0, 0, 0, 0, 0, 0 [STALL PROTECTION] stall_protection = 1 ; Alpha Protection off_limit = 30 ; Alpha below which the Alpha Protection can be disabled (If also below off_yoke_limit) off_yoke_limit = 1 ; Yoke position (in Pct) below which the Alpha Protection can be disabled (If also below off_limit) on_limit = 50 ; Alpha above which the Alpha Protection timer starts on_goal = 30 ; The alpha that the Alpha Protection will attempt to reach when triggered timer_trigger = 50.0 ; Duration (in Sec) the alpha must be above on_limit before the Alpha Protection is triggered ;===================== FLAPS ===================== [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 span-outboard = 0.8 ; Outboard span area (added area) (percentage, non dimensional) extending-time = 25 ; Flap extension time (SECONDS) damaging-speed = 233 ; Speed above which flap is damaged (Kts) blowout-speed = 250 ; Speed above which flap is blown out (Kts) maneuvering_flaps = 0 ;delay_between_flap_index = 0 lift_scalar = 0 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned) drag_scalar = 0 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned) pitch_scalar = 0 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned) max_on_ground_position = 5 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found. ;Flap section index number, flap position in degrees, airspeed limit, drag scalar, lift scalar, area scalar, add camber (radians), add aft feet (pos value moves center of lift forward), add incidence - scalar setting proportion of additional lift added at 0 degrees AOA (with 100% at stall AOA) flaps-position.0 = 0.00, -1, 0.00, 0.00 ; CONF 0 flaps-position.1 = 0.01, -1, 1.00, 1.00 ; CONF 1 flaps-position.2 = 10.00, 215, 1.00, 1.00 ; CONF 1+F flaps-position.3 = 15.00, 200, 1.00, 1.00 ; CONF 2 flaps-position.4 = 20.00, 185, 1.00, 1.00 ; CONF 3 flaps-position.5 = 40.00, 177, 1.00, 1.00 ; CONF FULL [FLAPS.1] 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 span-outboard = 0.8 ; Outboard span area (added area) (percentage, non dimensional) extending-time = 20 ; Flap extension time (SECONDS) damaging-speed = 233 ; Speed above which flap is damaged (Kts) blowout-speed = 250 ; Speed above which flap is blown out (Kts) maneuvering_flaps = 0 lift_scalar = 1 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned) drag_scalar = 1 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned) pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned) max_on_ground_position = 5 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found. ;Flap section index number, flap position in degrees, airspeed limit, drag scalar, lift scalar, area scalar, add camber (radians), add aft feet (pos value moves center of lift forward), add incidence - scalar setting proportion of additional lift added at 0 degrees AOA (with 100% at stall AOA) flaps-position.0 = 0.00, -1, 0.00, 0.00 ; CONF 0 flaps-position.1 = 5.0, -1, 0.30, 0.01 ; CONF 1 flaps-position.2 = 10.00, 215, 0.63, 1.30 ; CONF 1+F flaps-position.3 = 15.00, 200, 0.85, 1.30 ; CONF 2 flaps-position.4 = 20.00, 185, 0.97, 1.17 ; CONF 3 flaps-position.5 = 40.00, 177, 0.939, 1.00 ; CONF FULL [FLAPS.2] 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 span-outboard = 0.75 ; Outboard span area (added area) (percentage, non dimensional) extending-time = 20; Flap extension time (SECONDS) damaging-speed = 260 ; Speed above which flap is damaged (Kts) blowout-speed = 270 ; Speed above which flap is blown out (Kts) maneuvering_flaps = 0 lift_scalar = 0.01 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned) drag_scalar = 0.5 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned) pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned) max_on_ground_position = 5 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found. ;Flap section index number, flap position in degrees, airspeed limit, drag scalar, lift scalar, area scalar, add camber (radians), add aft feet (pos value moves center of lift forward), add incidence - scalar setting proportion of additional lift added at 0 degrees AOA (with 100% at stall AOA) flaps-position.0 = 0.00, -1, 1.00, 1.00 ; CONF 0 flaps-position.1 = 18.00, 230, 0.33, 1.00 ; CONF 1 flaps-position.2 = 18.01, 230, 0.63, 1.00 ; CONF 1+F flaps-position.3 = 22.00, 200, 0.85, 1.00 ; CONF 2 flaps-position.4 = 22.01, 185, 0.97, 1.00 ; CONF 3 flaps-position.5 = 27.00, 177, 0.939, 1.00 ; CONF FULL