// iss.0601211900 - v0_6 - inverters reworked. for a/c v0.1
// Font=Verdana,10pt. regular:: -{ nnn }- indicates *.air file section::
[fltsim.0]
title=Sparrowjet
sim=M77
model=
panel=
sound=
texture=
kb_checklists= M77_check
kb_reference= M77_ref
atc_id_enable=1
atc_id=G-ADNL
atc_airline=
ui_manufacturer=Miles
ui_type=M77 Sparrowjet
ui_variation=No. 92
description="A single seat jet racing aircraft made by modifying a Miles M5 Sparrowhawk to use the newly available Turbomeca Palas engines. It retaned the G-ADNL registration. First flight 14/12/1953 it won the SBAC Challenge Cup on 21/5/1956 and the King's Cup race on 13/7/1957 with a speed of 228 mph. It was destroyed in a hangar fire at RAF. Upavon in 1964."
visual_damage=0
[General]
atc_type=Miles
atc_model=Sparrowjet
editable=1
performance="Maximum Speed : 230 mph. 200 kts.\nCruise Speed: 220 mph. 191 kts.\nEngine: 2 x Turbomeca Palas 330 lb. static\nFuel Capacity: 84 gal. Imp. 50 gal. US.\nEmpty Weight: 1,578 lb. \nMaximum Gross Weight: 2,400 lb. \nLength: 28 ft, 4 in \nWingspan: 28 ft, 7 in. \nHeight: 7 ft, 2 in.\n"
[flight_tuning]
cruise_lift_scalar = 0.7
parasite_drag_scalar = 0.9
induced_drag_scalar = 1.0
elevator_effectiveness = 1.0
aileron_effectiveness = 1.0
rudder_effectiveness = 1.0
pitch_stability = 1.0
roll_stability = 1.0
yaw_stability = 1.0
elevator_trim_effectiveness = 2.0
aileron_trim_effectiveness = 1.0
rudder_trim_effectiveness = 1.0
p_factor_on_yaw = 1.0
[WEIGHT_AND_BALANCE]
max_gross_weight = 2400 // (pounds)
empty_weight = 1570 // (pounds)
reference_datum_position = 0, 0, 0 // (feet) distance from FlightSim Reference position:
empty_weight_CG_position = 0, 0, 0 // (feet) long, lat, vert distance from specified datum.
max_number_of_stations = 3
station_load.0 = "155, 5.5, 0.0, -0.6, Pilot" // Weight (lbs), long, lat, vert. (feet)
;Moments of Inertia
empty_weight_pitch_MOI = 1121
empty_weight_roll_MOI = 616
empty_weight_yaw_MOI = 1532
empty_weight_coupled_MOI= 0.0
[GeneralEngineData]
engine_type = 1 // 1=Jet
Engine.0 = -1.2, -2.2, -0.8 // (feet) long, lat, vert.
Engine.1 = -1.2, 2.2, -0.8
fuel_flow_scalar = 1.0 // Fuel flow scalar
min_throttle_limit = 0.0 // Minimum percent throttle.
[TurbineEngineData]
fuel_flow_gain = 0.0025
inlet_area = 0.3 // (sq.ft.)
rated_N2_rpm = 35500 // rpm @ 100% [34,000 actual]
static_thrust = 330 // (Dry)
afterburner_available = 0
reverser_available = 0
[jet_engine]
thrust_scalar = 1.2
[airplane_geometry]
wing_area = 159.0 // Square feet [Gross ]
wing_span = 28.6 // Feet
wing_root_chord = 5.57 // Feet[ mean average chord ]
wing_dihedral = 7.0 // Degrees
wing_incidence = 0.0 // Degrees ( not used by fs9? )
wing_twist = 0.0 // Degrees
oswald_efficiency_factor = 0.75 // Measure of lift effeciency of wing.
wing_winglets_flag = 0 // Are winglets available?
wing_sweep = 1.0 // Degrees, on wing mean average chord.
wing_pos_apex_lon = 1.39 // Feet, negative going aft
wing_pos_apex_vert = -0.8 // Feet, positive going up.
htail_area = 19.32 // Square feet
htail_span = 9.12 // Feet.
htail_pos_lon = -13.58 // Feet, longitudinal distance from reference point, negative going aft
htail_pos_vert = 1.55 // Feet, vertical distance from reference point, positive going up
htail_incidence = -1.5 // Degrees.
htail_sweep = 0.0 // Degrees, horizontal on tail mean average chord.
vtail_area = 7.03 // Square feet.
vtail_span = 3.4 // Feet, tip to body.
vtail_sweep = 0.0 // Degrees, on vertical tail mean average chord.
vtail_pos_lon = -14.2 // Feet, negative going aft.
vtail_pos_vert = 1.33 // Feet, positive going up.
elevator_area = 10.74 // Square feet.
aileron_area = 12.0
rudder_area = 8.79
elevator_up_limit = 28.0 // Degrees = 0.49 rad.
elevator_down_limit = 21.0 // Degrees = 0.37 rad.
aileron_up_limit = 20.0 // Degrees = 0.35 rad.
aileron_down_limit = 15.0 // Degrees = 0.26 rad.
rudder_limit = 25.0 // Degrees = 0.44 rad. Keyframe action referenced to this, Do not change.
elevator_trim_limit = 19.5 // Degrees = 0.34 rad.
spoiler_limit = 0.0 // Degrees.
spoilerons_available = 0 // Spoilerons Available?
aileron_to_spoileron_gain = 0
min_ailerons_for_spoilerons = 0
min_flaps_for_spoilerons = 0
[Reference Speeds]
flaps_up_stall_speed = 52.0 // Knots True (KTAS) = 60 mph. actual.
full_flaps_stall_speed = 43.0 // (KTAS) = 50 mph. estimated.
cruise_speed = 191.0 // (KTAS) = 220 mph. @ 10,000 ft.
max_indicated_speed = 200.0 // Red line (KIAS) = 230 mph.
max_mach=0.315381
[contact_points]
// GEAR --{1004}--
point.0 = 1, -15.00, 0.00, -0.93, 1378.0, 0, 0.42, 45, 0.25, 2.5, 0.8, 0, 0, 7, 0, 0
point.1 = 1, 1.75, -3.75, -2.85, 1968.5, 1, 0.55, 0, 0.15, 1.0, 0.5, 0, 0, 2, 0, 0
point.2 = 1, 1.75, 3.75, -2.85, 1968.5, 2, 0.55, 0, 0.15, 1.0 0.5, 0, 0, 3, 0, 0
// SCRAPES --{1005}--
point.3 = 2, -3.23, -14.67, 0.00, 1200.0, 0, 0.0, 0, 0.0, 0.0, 0.0, 0, 0, 5
point.4 = 2, -3.23, 14.67, 0.00, 1200.0, 0, 0.0, 0, 0.0, 0.0, 0.0, 0, 0, 6
point.5 = 2, -17.77, 0.00, 0.00, 1200.0, 0, 0.0, 0, 0.0, 0.0, 0.0, 0, 0, 9
point.6 = 2, 12.90, 0.00, 0.00, 1200.0, 0, 0.0, 0, 0.0, 0.0, 0.0, 0, 0, 4
max_number_of_points = 8
static_pitch = 6.8 // --{301}--
static_cg_height = 2.47 // 49232= 2.47
gear_system_type = 0 // --{523}--
[brakes]
parking_brake = 1 // Parking brake available.
toe_brakes_scale = 0.6 // Brake scalar.
differential_braking_scale = 0.3 // Delta on the amount of brake when the rudder pedals are deflected.
[flaps.0] //Trailing Edge Flaps
type = 1 // 1 - tail
span-outboard = 0.45 // 0.0 .. 1.0
extending-time = 5 // seconds
flaps-position.0 = 0 // degrees [guesses]
flaps-position.1 = 10 // degrees = 0.17 rad.
flaps-position.2 = 30 // degrees = 0.52 rad.
flaps-position.3 = 60 // degrees = 1.05 rad.
damaging-speed = 95 // KIAS
blowout-speed = 270 // KIAS
lift_scalar = 1.0
drag_scalar = 0.8
pitch_scalar = 0.3
system_type = 0 // 0 = electric.
[electrical]
engine_generator_map= 0,0
max_battery_voltage= 28.0
;BusType, MaxAmpLoad, MinVoltage BusTypes:0=MainBus,1=AvionicsBus,2=BatteryBus,3=HotBatteryBus,4-7=Generator/AlternatorBus(1-4)
avionics_bus = 0, 0.5, 17.0
avionics = 1, 0.5 17.0
additional_system = 0, 0.5, 17.0 // Only fuel gauges.[ Inverters use Landingq lights to simulate batt. drain.]
starter1 = 0, 0, 17.0 // No starter motors were fitted.
starter2 = 0, 0, 17.0
[Views]
eyepoint= 5.0, 0.0, 1.82 // (feet) long, lat, vert, distance from reference datum.
[LIGHTS]
//Types: 5=landing. This is to simulate inj. power.
light.0 = 5, 0.0, 0.0, 0.0, fx_landing
[keyboard_response]
//Breakpoint speeds (knots) on the keyboard increments of control surfaces.
//Speed at which the incremenet is reduced to 1/2 and 1/8 respectively.
elevator = 100, 180
aileron = 200, 1000
rudder = 200, 1000
[fuel]
LeftMain = 0.0, -4.2, -0.6, 50.4, 0.0 // Long. (feet), Lat, Vert, Usable(gallons US), Unusable .
RightMain = 0.0, 4.2, -0.6, 50.4, 0.0 // 42 imp.
fuel_type = 2 // Fuel type: 2=JetA.[ Was actally Kerosene ]
number_of_tank_selectors = 1
electric_pump = 1
[Radios] // No radio was fitted; this is the minimum to be able to use ATC in fs9.
// Radio Type = availiable, standby frequency, has glide slope.
Audio.1 = 1
Com.1 = 1, 0
Nav.1 = 0, 0, 0
Adf.1 = 0
Transponder.1 = 1
Marker.1 = 0
[EFFECTS]
wake=fx_wake
water=fx_spray
dirt=fx_tchdrt
concrete=fx_sparks
touchdown=fx_tchdwn_s, 1
[hydraulic_system]
engine_map= 0,0
normal_pressure = 0.0 // PSI - none fitted.
[stall_warning]
type=0
[direction_indicators]
//1 Type: 1=Vacuum
direction_indicator.0= 1
[attitude_indicators]
//Type: 1=Vacuum Gyro
attitude_indicator.0 = 1
[turn_indicators]
//Type: 2= Vacuum Gyro
turn_indicator.0= 2,2 // Turn AND Bank.
[autopilot]
autopilot_available= 0
flight_director_available= 0
[forcefeedback] // A copy of the Extra - You are on your own here!
ground_bumps_magnitude1=3000 ; 0 - 10000
ground_bumps_angle1=8900 ; 0 - 35999 degrees
ground_bumps_intercept1=4.0
ground_bumps_slope1=0.25
ground_bumps_magnitude2=350 ; 0 - 10000
ground_bumps_angle2=9100 ; 0 - 35999 degrees
ground_bumps_intercept2=0.075
ground_bumps_slope2=0.7
crash_magnitude1=10000 ; 0 - 10000
crash_direction1=01000 ; 0 - 35999 degrees
crash_magnitude2=10000 ; 0 - 10000
crash_direction2=9000 ; 0 - 35999 degrees
crash_period2=75000 ; in microseconds
crash_duration2=2500000 ; in microseconds
