[fltsim.0]
title=ParaFoil
sim=ParaFoil
model=
panel=
sound=
texture=
kb_checklists=Parafoil_check
kb_reference=Parafoil_ref
atc_id=N0PF
ui_manufacturer=Tango Golf Aeronautics
ui_type="ParaFoil"

description="This is representative of the early ram-air-wing type of gliding parachutes developed in the early 1970's. To deploy it, use Map on the World Menu to put it at 5,000 to 10,000 ft above the surface. It steers with roll control.  Use flaps to flare before landing or to come down steeply. Canopy design and FD files copyright 2004 by Tom Goodrick."

[General]
atc_type=Schweizer
atc_model=2-32
editable=0
performance="Maximum Speed\t\n137 kts            158 mph          254 kmh\n\nEngine\t\nnone\n\nGlide Ratio\t\n36 to 1\n\nEmpty Weight\t\n1000 lb              454 kg\n\nLength\t\n26.75 ft \t          8.78 m\n\nWingspan\n57 ft\t          18.7 m\n\nWing Area\t\n180 sq ft \t          19.37 m2\n\nAspect Ratio\t\n18.05\n\nMaximum L\/D (Calculated) \t\n~57 kts            ~66 mph          ~106 kmh\n\nMinimum Sink (Calculated) \t\n~47 kts            ~54 mph\t     ~87 kmh\n\nSeating\t\nUp to 2\n\nUseful Load\t\n430 lb \t195 kg"


[WEIGHT_AND_BALANCE]
max_gross_weight = 250                         // (pounds)
empty_weight = 50                             // (pounds)

reference_datum_position     =  1.25, 0, 0      // (feet) distance from FlightSim Reference position: (1/4 chord, centerline, waterline)
empty_weight_CG_position     = -0.80, 0, -2.0      // (feet) longitudinal, lateral, vertical distance from specified datum

max_number_of_stations = 50

station_load.0 = "200, -0.20,  0.0, -8.0, Pilot"              //       Weight (lbs), longitudinal, lateral, vertical positions from datum (feet)


;Moments of Inertia
empty_weight_pitch_MOI   = 2000
empty_weight_roll_MOI    = 2000
empty_weight_yaw_MOI     = 500
empty_weight_coupled_MOI = 0.0


[electrical]
electric_always_available=1

[flight_tuning]

parasite_drag_scalar   = 0.8
induced_drag_scalar    = 1.0
elevator_effectiveness = 0.0
aileron_effectiveness  = 1.0
rudder_effectiveness   = 0.0
pitch_stability        = 1.0
roll_stability         = 1.0
yaw_stability          = 1.0
elevator_trim_effectiveness = 1.0
aileron_trim_effectiveness  = 1.0
rudder_trim_effectiveness   = 1.0

[SMOKESYSTEM]
smoke.0= 0.0, -10.0, 0.0, fx_smoke_w

[GeneralEngineData]
engine_type = 2                                 //0=Piston, 1=Jet, 2=None, 3=Helo-Turbine, 4=Rocket, 5=Turboprop
fuel_flow_scalar = 0                            //Fuel flow scalar

[pitot_static]
vertical_speed_time_constant = 4                //Increasing this value will cause a more instantaneous reaction in the VSI


        //0  Class
        //1  Longitudinal Position        (feet)
        //2  Lateral Position             (feet)
        //3  Vertical Position            (feet)
        //4  Impact Damage Threshold      (Feet Per Minute)
        //5  Brake Map                   (0=None, 1=Left, 2=Right)
        //6  Wheel Radius                (feet)
        //7  Steer Angle                         (degrees)
        //8  Static Compression           (feet)  (0 if rigid)
        //9  Max/Static Compression Ratio
        //10 Damping Ratio               (0=Undamped, 1=Critically Damped)
        //11 Extension Time              (seconds)
        //12 Retraction Time             (seconds)
        //13 Sound Type
        
[contact_points]
point.0=1,  -.9,    0.0, -13.25, 3500.0, 0, 0.509, 0.0, 0.90, 2.5, 0.95, 0.0, 0.0, 3, 0.0, 0.0
point.1=2,  -1.25, -11.5,  0.5,  787.4, 0, 0.000, 0.0, 0.00, 0.0, 0.00, 0.0, 0.0, 5, 0.0, 0.0
point.2=2,  -1.25,  11.5,  0.5,  787.4, 0, 0.000, 0.0, 0.00, 0.0, 0.00, 0.0, 0.0, 6, 0.0, 0.0
point.3=2, -8.42,   0.0, -0.7,  787.4, 0, 0.000, 0.0, 0.00, 0.0, 0.00, 0.0, 0.0, 9, 0.0, 0.0
point.4=2,   0.25,   0.0, -2.2,  787.4, 0, 0.000, 0.0, 0.00, 0.0, 0.00, 0.0, 0.0, 4, 0.0, 0.0

static_pitch = -4
static_cg_height = 12.9

[brakes]
parking_brake = 1        //Parking brake available
toe_brakes_scale = 0.67  //Brake scalar

[fuel]
electric_pump=0
fuel_type = 1                                //Fuel type: 1 = Avgas, 2 = JetA

[hydraulic_system]
normal_pressure = 0.0    //PSI

[Views]
eyepoint = 1.063, 0.0, 1.435

[LIGHTS]
//Types: 1=beacon, 2=strobe, 3=navigation, 4=cockpit, 5=landing
light.0 = 4,  2.7,   0.00,  1.50, fx_vclight,

[flaps.0]
type             = 1                                    // 1 - tail, 2 - lead
span-outboard    = 0.5                                  // 0.0 .. 1.0
extending-time   = 3                                    // seconds
flaps-position.0 = 0
flaps-position.1 = 20
flaps-position.2 = 40                                    // degrees, KIAS
damaging-speed   = 250                                  // KIAS
blowout-speed    = 300

[Radios]
// Radio Type = availiable, standby frequency, has glide slope
Audio.1       = 0
Com.1         = 1, 0
Nav.1         = 0, 0, 0
Adf.1         = 0
Transponder.1 = 0
Marker.1      = 0

[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 = 160, 360
aileron  = 160, 360
rudder   = 160, 360

[direction_indicators]
//1 Type: 0=None, 1=Vacuum Gyro, 2=Electric Gyro, 3=Electro-Mag Slaved Compass, 4=Slaved to another
//2 Indicator number of slaving indicator if Type = 4
direction_indicator.0=0,0

[attitude_indicators]
//Type: 0=None, 1=Vacuum Gyro, 2=Electric Gyro
attitude_indicator.0 = 0

[turn_indicators]
//Type: 0=None, 1=Electric Gyro, 2= Vacuum Gyro
turn_indicator.0=0,0

[EFFECTS]
wake=fx_wake
water=fx_spray
dirt=fx_tchdrt
concrete=fx_tchdwn_s

[airplane_geometry]
wing_area               = 250.0                 //Square feet
wing_span               = 25.0                  //Feet
wing_root_chord         = 10                   //Feet
wing_dihedral           = 1.0                   //Degrees
wing_incidence          = 3.0                   //Degrees
wing_twist              = 0.0                  //Degrees
oswald_efficiency_factor= 0.6                   //Measure of lift effeciency of wing
wing_winglets_flag      = 0                     //Are winglets available?
wing_sweep              = 0.0                   //Degrees, wing leading edge
wing_pos_apex_lon       = 1.25                  //Feet, longitudinal distance from reference point, negative going aft
wing_pos_apex_vert      = 11.3                   //Feet, vertical distance from reference point, positive going up
htail_area              = 21.0                  //Square feet
htail_span              = 7.9                   //Feet
htail_pos_lon           = -8.75                 //Feet, longitudinal distance from reference point, negative going aft
htail_pos_vert          = 0.0                   //Feet, vertical distance from reference point, positive going up
htail_incidence         = -1.0                   //Degrees
htail_sweep             = 0.0                   //Degrees, horizontal tail leading edge
vtail_area              = 17.0                  //Square feet
vtail_span              = 4.7                   //Feet, tip to body
vtail_sweep             = 0.0                   //Degrees, vertical tail leading edge
vtail_pos_lon           = -8.0                 //Feet, longitudinal distance from reference point, negative going aft
vtail_pos_vert          = 3.9                   //Feet, vertical distance from reference point, positive going up
elevator_area           = 12.0                  //Square feet
aileron_area            = 14.7                  //Square feet
rudder_area             = 18.0                   //Square feet
elevator_up_limit       = 0.01                  //Degrees
elevator_down_limit     = 0.01                  //Degrees
aileron_up_limit        = 0.0                  //Degrees
aileron_down_limit      = 40.0                  //Degrees
rudder_limit            = 40.0                  //Degrees
elevator_trim_limit     = 15.0                  //Degrees
spoiler_limit           = 0.0                  //Degrees
spoilerons_available    = 0                     //Spoilerons Available?
aileron_to_spoileron_gain = 0                   //Aileron to spoileron gain
min_ailerons_for_spoilerons = 0                 //Degrees
min_flaps_for_spoilerons = 0                    //Minimum flap handle position when spoilerons activate

[Reference Speeds]
flaps_up_stall_speed    = 40.0                  //Knots True (KTAS)
full_flaps_stall_speed  = 40.0                  //Knots True (KTAS)
cruise_speed            = 47.0                  //Knots True (KTAS)
max_indicated_speed     = 158                   //Red line (KIAS)

[autopilot]
autopilot_available= 0
flight_director_available= 0

[forcefeedback]
ground_bumps_magnitude1=2500            ; 0 - 10000
ground_bumps_angle1=8900                ; 0 - 35999 degrees
ground_bumps_intercept1=10.0
ground_bumps_slope1=0.300
ground_bumps_magnitude2=350             ; 0 - 10000
ground_bumps_angle2=9100                ; 0 - 35999 degrees
ground_bumps_intercept2=0.075
ground_bumps_slope2=1.0
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

[yaw_string]
yaw_string_available=1

[stall_warning]
type=1