Aircraft Configuration Files

 
Any errors made in creating or editing the aircraft.cfg file will showup, along with the following error messages, while an aircraft is beingloaded. The error messages are listed in order; that is, the firsterror message represents an error early in the aircraft-loading process.

Error Message	Description
Aircraftinitialization failure.	Indicatesthat some essential files are missing from the aircraftcontainer. If the files are missing, the aircraft will not usually bedisplayed in the Aircraft Selection Screen; as a result, this error israre.
Failedto start up the flight model.	The.air file was not loaded successfully.
Thisis not a Flight Simulator aircraft model.	Thevisual model (.mdl) file for this aircraft is not compatible with Flight Sim World
Visualmodel could not be displayed.	Anerror occurred while loading the visual model (.mdl) file.

      

Datum Reference Point

Positions of aircraft components are given relative to the datum reference point for the aircraft, in the order: longitudinal, lateral, vertical. The convention for positions is positive equals forward, to the right, and vertically upward. Units are in feet. The datum reference point itself is specified in the weight_and_balance section.

 

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Sections of the Configuration File

New and Changed for Flight Sim World

[fltsim.n]

Additional Sections

[antidetonation system.n]

Property	Description	Examples
reservoir_size	Gallons.	reservoir_size = 4
flow_rate	Gallons per minute.	flow_rate = 3.
reservoir_position	Position relative to datum reference point .	reservoir_position = -1.8, 4.1, -1.8
max_mp_compensate	Manifold pressure above which AntiDetonation system cannot compensate for. Units are inches of mercury.	max_mp_compensate = 135

[nitrous system.n]

Property	Description	Examples
reservoir_size	Gallons	reservoir_size=10.0
flow_rate	Gallons per minute	flow_rate=5.0
mp_boost	Multiplier on manifold pressure	mp_boost=1.75

[tailhook]

Property	Description	Examples
tailhook_length	Length of tailhook in feet.	tailhook_length = 4.5
tailhook_position	Tailhook pivot point relative to datum reference point .	tailhook_position = -49.0, 0, -2.5

[voicealerts]

Property	Description	Examples
lowfuelpct	Three values: Low Fuel limit (percent), check above (1) or below (-1), and check every N seconds.	LowFuelPct = 0.1, -1, 60
overglimit	High G limit, check above (1) or below (-1), and check every N seconds.	OverGLimit = 6.0, 1, 1 )

 

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Standard Sections

[fltsim.n]

Each [fltsim.n]section of an aircraft configuration file represents adifferent version (configuration) of the aircraft, and is known as aconfiguration set. Configuration sets allow a single aircraft containerto represent several aircraft, and allow those aircraft to sharecomponents.

If there is only one section (labeled [fltsim.0]), it isbecause there is only one configuration set in that aircraft container.If there is more than one configuration set (labeled [fltsim.0], [fltsim.1], [fltsim.2], and soon), each one refers to a different version of the aircraft.

For instance, there are several versions of the Diamond DA42,allhoused in the same DA42 aircraft container (folder). Thevarious versions must vary by their title, and may also vary otheritems such as the panel, description, and sounds.

While these configuration sets share many components, they caneach use different panels. The panel=line in the respective fltsim sections thus refer to therespective panel folderfor each aircraft:  For example, panel=g1000 means thatthis version of the DA42 uses the panel files in the panel.g1000 subfolder.

When creating and referencing multiple model, panel, sound,and texture directories, use the naming conventionfoldername.extension,where the extension is a unique identifier forthat configuration set (for example, .g1000). To refer to the folder fromtherelevant parameter in the aircraft.cfg file, just specify the extension(for example, panel=g1000).If a parameter is not explicitly set it automatically referstothe default (extension-less) folder.

The parameters in each configuration set can refer to the samefiles, to different files, or to a mix of files. While using differentpanels, all DA42 configurations use the same sounds, and thus thesound parameters in all the fltsim sections point to thesingle soundfolder in the DA42 folder.

Each aircraft defined by a configuration set will appear as aseparate listing in the Aircraft livery screen. From a user’s perspective, they are distinctaircraft (just as if all the common files were duplicated and includedin three distinct aircraft containers). From a developer’sperspective, the aircraft are really just different configuration setsof the same aircraft. Because they share some files, they make muchmore efficient use of disk space.

Within each[fltsim.n] section are parameters that define thedetails of that particular configuration set:

Property	Description	Examples
title	The title of the aircraft.	Diamond DA42 ( title=Diamond DA42 Twin Star ) Piper PA28( title=Piper PA-28 Cherokee 180 )
sim	Specifies which .air (flight model) file (located inthe aircraft folder) to use.	Diamond DA42 ( sim=DA42 ) Piper PA28 ( sim=Piper_PA28_180)
model	Specifies which model folder to reference. If no entryis made, the default folder is used.	Diamond DA42 ( model= )
panel	Specifies which panel folder to reference.	Diamond DA42 ( panel= )
sound	Specifies which sound folder to reference.	Diamond DA42 ( sound= )
texture	Specifies which texture folder to reference.	Diamond DA42 ( texture=2) Piper PA28 ( texture= )
kb_checklists	Deprecated, leave blank.	kb_checklists=
kb_reference	Deprecated, leave blank.	kb_reference=
atc_id	The tail number displayed on the exterior of theaircraft. Note thatcustom tail numbers burned into textures will not be modified bythis.	Diamond DA42( atc_id="N42DA" )
atc_id_color	This is the colour which will be used to render the tail number. This is a hexadecimal number using ARGB format.	E.g atc_id_color=0xFF0FF00 for pure green.
atc_id_font	This is the font name used for rendering the tail number. The font name must correspond to an entry in Fonts/fonts.json file.	atc_id_font="ARIAL BLACK"
atc_id_render_target_width	This is the width of the render target which will be created to render the tail number. Note that AI aircraft will have this size divided by 2 (e.g. 512)	atc_id_render_target_width=1024
atc_airline	The ATC system will use the specified airline name withthis aircraft. This is dependant on ATC recognizing the name. ATC willtreat this aircraft as an airliner when this is used in conjunctionwith atc_flight_number.	atc_airline="Airline Name"
atc_flight_number	The ATC system will use this number as part of theaircrafts callsign. ATC will treat this aircraft as an airliner whenthis is used in conjunction with atc_airline.	atc_flight_number=1123
ui_manufacturer	This value identifies the manufacturer sub-categoryused to group aircraft in the select aircraft dialog inside Flight Sim World.	ui_manufacturer="Diamond"  ui_manufacturer="Piper"
ui_type	This value identifies the type sub-category used togroup aircraft in the select aircraft dialog inside Flight Sim World.	ui_type=DA42 Twin Star
ui_variation	This value identifies the variation sub-category usedto group aircraft in the select aircraft dialog inside Flight Sim World.	ui_variation="@IDS_AIRCRAFT_LIVERY_TYPE_STRIPE_2"
ui_typerole	This value identifies the role of the aircraft.	ui_typerole="@IDS_TYPE_TWIN_PROP" ui_typerole="Commercial Airliner"
ui_createdby	This value is used to identify the creator of theconfiguration file.	ui_createdby="Dovetail Games"
ui_thumbnailfile	Path to the livery specific image to display as a thumbnail in the UI. 600x240 as PNG or JPEG.	ui_thumbnailfile="texture.1\thumbnail.png"
ui_hangarfile	Path to the livery specific image to display when the livery is selected in the livery selection screen. 1920x1080 as PNG or JPEG.	ui_hangarfile="texture.1\hangar.png"
ui_selectionfile	Path to the livery specific image to display as the background in the hangar when the aircraft is hovered over. 1920x1080 as PNG or JPEG.	ui_selectionfile="texture.1\selection.png"
ui_tilefile	Path to the livery specific image to display on the flight planner tile when the aircraft is selected. 210x44 as PNG or JPEG or the Hangar File can be reused here.	ui_tilefile="texture.1\hangar.png"
ui_visible	If this livery (not aircraft) is visible in the UI. Useful for hiding liveries only used for AI or missions.	ui_visible=TRUE ui_visible=FALSE
atc_heavy	Setting this flag to 1 will result in the ATC systemappending the phrase heavy to the aircrafts callsign.	atc_heavy=0 atc_heavy=1
atc_parking_types	Specifies the preferred parking for this aircraft, usedby ATC. If this line is omitted, ATC will determine parking accordingto the type of aircraft and parking available. If multiple values arelisted, preference will be given in the order in which they are listed.The valid values may be one or more of the following: RAMP, CARGO,GATE, DOCK, MIL_CARGO, MIL_COMBAT.	atc_parking_types=RAMP atc_parking_types=CARGO atc_parking_types=GATE,RAMP
atc_parking_codes	Specifies one or more ICAO airline designations so that ATC can direct the aircraft to a gate that has also been designated specifically for that same airline, for example, "DTA" for Dovetail Airlines.	Refer to the example XML for the TaxiwayParking entry in the Compiling BGL document. The codes entered in the airlineCodes entry should match the text entered here. The ICAO codes do not have to be used, and can be as short as one character, as long as the text strings match, but for clarity use of the ICAO codes is recommended. If mutliple parking codes are entered, separate them with commas.

[general]

In addition to the fltsim sections, the generalsectioncontains information related to all variations of the aircraft. Forexample, the Cessna 182RG, 182S, and 182S IFR are all the same type ofaircraft, and contain the same flight model. As such,there are some things that are not variableacross variations:

Property	Description	Examples
atc_type	This is the specific aircraft type that the ATC systemrecognizes for this type of aircraft.	atc_type=Piper atc_type=Diamond
atc_model	This is the specific aircraft model that the ATC systemrecognizes for this type of aircraft. Note: atc_type + atc_model when combined should be unique to an aircraft.	atc_model=PA28 atc_model=DA42 atc_model=P28R
category	For aircraft, one of airplane or helicopter.	Category = airplane Category = Helicopter
ai_selection_bias	This should always be 0.0	ai_selection_bias=0.0

[pitot_static]

The vertical_speed_time_constant parameter can be used to tunethe lag of the Vertical Speed Indicator for the aircraft:

• Increasing the time constant decreases the lag, making thegauge react more quickly.
• Decreasing the time constant increases the lag, making thegauge react more slowly.
• A value of 0 effectively causes the indication to freeze.If an instantaneous indication is desired, use an excessively largevalue, such as 99.
• If the line is omitted, the default value is 2.0.

Property	Description	Examples
vertical_speed_time_constant	Increases or decreases the lag of the vertical speedindicator. Increasing will cause a more instantaneous reaction in theVSI.	vertical_speed_time_constant = 1  vertical_speed_time_constant = 1.0 vertical_speed_time_constant = 4
pitot_heat	Scale of heat effectiveness, or 0 if not available.	pitot_heat = 1.0 pitot_heat=0.000000 pitot_heat = 0.

[weight_and_balance]

The weight and center of gravity of the aircraft can beaffected through thefollowing parameters.

 

Note

In the stock aircraft, the station_load.0, 1, etc. parameters are enclosed in quotation marks.  These are used by internallanguage translation tools.

 

Moments of Inertia

A moment of inertia (MOI) defines the mass distribution aboutan axis of an aircraft. A moment of inertia for a particular axis isincreased as mass is increased and/or as the given mass is distributedfarther from the axis. This is largely what determines the inertialcharacteristics of the aircraft.

The following weight and balance parameters define the MOIs of theempty aircraft, so the values should not reflect fuel,passengers or baggage. The simulation engine determines the total MOIs with these additional, and variable, influences. The units are slugs per foot squared.Omission of a parameter will result in the use of a default value set in the .air file, if one exists.
These values can be estimated with the following formula:

• MOI = EmptyWeight * (D^2 / K)

Where:

	Pitch	Roll	Yaw
D=	Length(feet)	Wingspan(feet)	0.5*(Length+Wingspan)
K =	810	1870	770

This formula yields only rough estimates. Actual values vary based onaircraft material, installed equipment, and number of engines and theirpositions.

Property	Description	Examples
max_gross_weight	Maximum design gross weight of the aircraft.	max_gross_weight = 150000  max_gross_weight= 600.000  max_gross_weight = 875000  max_gross_weight = 5524
empty_weight	Total weight (in pounds) of the aircraft minus usable fuel, passengers, and cargo. If not specified, the value previously set in the .air file will be used.	empty_weight = 74170  empty_weight= 310.000  empty_weight = 394088  empty_weight = 3911
reference_datum_position	Offset (in feet) of the aircraft's reference datum from the standard Flight Sim World center point, which is on the centerline chord aft of the leading edge. By setting the Reference Datum Position, actual aircraft loading data can be used directly according to the aircraft's manufacturer. If not specified, the default is 0,0,0.	reference_datum_position= 0.000, 0.000, 0.000  reference_datum_position = 83.5, 0, 0  reference_datum_position = 6.96, 0, 0
empty_weight_cg_position	Offset (in feet) of the center of gravity of the basic empty aircraft (no fuel, passengers, or baggage) from the datum reference point .	empty_weight_CG_position= 0.000, 0.000, 0.000  empty_weight_CG_position = -90.5, 0, 0  empty_weight_CG_position = -6.06, 0, 0
max_number_of_stations	Specifies the maximum number of stations Flight Sim World will calculate when the aircraft is loaded. This allows an unlimited number of stations to be specified. Note that an excessively large number here results in a longer load time for the aircraft when selected, although there is no effect on real-time performance.	max_number_of_stations = 50
station_load.0 to station_load.n	Specifies the weight and position of passengers or payload at a station specified with a unique number, station_load.N. Parameters in order are: active, Filled Weight (lbs), Max Weight (lbs),longitudinal, lateral, vertical positions from datum (feet), passenger index. Where long, lat and vertical positions are relative to the datum reference point. The addition of stations results in a corresponding change in aircraft flight dynamics due to the change of the total weight and moments of inertia. Active states if the payload has its filled weight by default before the payload amounts are adjusted. Usually Pilot (potentially also copilot) and some Baggage would be active by default on a GA aircraft. For the passenger index the numbers are as follows: -1 = Not a person (baggage etc) 0 = Pilot 1, 2 ,3 etc = Passengers, matching with those specified in the model.cfg for the aircraft.	station_load.0 = 1, 190, 350, -0.33, -0.90, 1.29, 0 station_load.3 = 0, 170, 350, -3.05, 0.90, 1.21, 3 station_load.5 = 1, 50,100, -4.54, -0.69, 0.42, -1
station_name.0 to station_name.n	This field is the string name that is used in the Payload dialog (15 character limit). Omission of this will result in a generic station name being used. Note that if passed a translation string e.g @IDS_ST_PILOT only the string ID is limited to 15 characters not the translated result.	station_name.0 = "Payload" station_name.1 = "@IDS_ST_PILOT"  station_name.0 = "Pilot" station_name.7 = "Forward Baggage"
empty_weight_pitch_moi	The moment of inertia (MOI) about the lateral axis.	empty_weight_pitch_MOI = 3172439  empty_weight_pitch_MOI= 230.000  empty_weight_pitch_MOI = 24223159  empty_weight_pitch_MOI = 3905.65
empty_weight_roll_moi	The moment of inertia (MOI) about the longitudinal axis.	empty_weight_roll_MOI = 2262183  empty_weight_roll_MOI= 205.000  empty_weight_roll_MOI = 13352310  empty_weight_roll_MOI = 2718.64
empty_weight_yaw_moi	The moment of inertia (MOI) about the vertical axis.	empty_weight_yaw_MOI = 3337024  empty_weight_yaw_MOI= 290.000  empty_weight_yaw_MOI = 39531785  empty_weight_yaw_MOI = 5291.04
empty_weight_coupled_moi	The moment of inertia (MOI) about the roll and yaw axis (usually zero).	empty_weight_coupled_MOI = 0  empty_weight_coupled_MOI= 0.000  empty_weight_coupled_MOI= 0.0  empty_weight_coupled_MOI = 0.0

[flight_tuning]

Flight control effectiveness parameters

The elevator, aileron and elevator effectiveness parametersaremultipliers on the default power of the control surfaces. Forexample, a value of 1.1 increasesthe effectiveness by 10 percent. Likewise, a value of 0.9 decreases theeffectiveness by 10 percent. A negative number reverses the normaleffect of the control. Omission of a parameter results in the defaultvalue of 1.0.

Stability parameters

The pitch, roll and yaw parameters are multipliers on thedefaultstability (damping effect) about the corresponding axis of theairplane. For example, a value of 1.1 increases the damping by 10%.Likewise, a value of 0.9 decreases the damping by 10%. A negativenumber results in an unstable characteristic about the axis. A positivedamping effect is simply a moment in the direction opposite of therotational velocity. Omission of a parameter will result in the defaultvalue of 1.0.

Lift parameter

The cruise_lift_scalar parameter is a multiplier on thecoefficient oflift at zero angle of attack Cruise lift in this context refers tothe lift at relatively small angles of attack, which is typical for anairplane in a cruise condition. This scaling is decreased linearly asangle of attack moves toward the critical (stall) angle of attack,which prevents destabilizing low speed and stall characteristics athigh angles of attack. Modify this value to set the angle of attack(and thus pitch) for a cruise condition. A negative value is notadvised, as this will result in extremely unnatural flightcharacteristics. Omission of this parameter results in thedefault value of 1.0.

High Angle of Attack parameters

The hi_alpha_on_roll and hi_alpha_on_yaw  parametersare multipliers on the effects onroll and yaw at high angles of attack.  The default values are1.0.

Propeller-induced turning effect parameters

The p_factor_on_yaw, torque_on_roll, gyro_precession_on_pitchandgyro_precession_on_yaw parameters are multipliers on the effectsinduced by rotating propellers. These are often called “leftturning tendencies” for clockwise rotating propellers. The simulation correctly handles counter-clockwise rotating propellers. The default values are 1.0.

Drag parameters

Drag is the aerodynamic force that determines the aircraftspeed and acceleration. There are two basic types of drag that the usercan adjust here. Parasitic drag is composed of two basic elements: formdrag, which results from the interference of streamlined airflow, andskin friction. Parasite drag increases as airspeed increases. Induceddrag results from the production of lift. Induced drag increases asangle of attack increases.

The parasite_drag_scalar and induced_drag_scalar parametersare multipliers on the two respectivedrag coefficients. For example, a value of 1.1 increases the respectivedrag component by 10 percent. A value of 0.9 decreases the drag by 10Percent. Negative values are not advised, as extremely unnatural flightcharacteristics will result.  The default values are 1.0.

Property	Description	Examples
cruise_lift_scalar	CL0.	cruise_lift_scalar = 1.0  cruise_lift_scalar=1.000
parasite_drag_scalar	Cd0.	parasite_drag_scalar = 1.0  parasite_drag_scalar=1.000
induced_drag_scalar	Cdi.	induced_drag_scalar = 1.0  induced_drag_scalar=1.000
elevator_effectiveness	Cmde.	elevator_effectiveness = 1.0  elevator_effectiveness=1.000
aileron_effectiveness	Clda.	aileron_effectiveness = 1.0  aileron_effectiveness=1.000
rudder_effectiveness	Cndr.	rudder_effectiveness = 1.0  rudder_effectiveness=0.501
pitch_stability	Cmq.	pitch_stability = 1.0  pitch_stability=1.000
roll_stability	Clp.	roll_stability = 1.0  roll_stability=1.000
yaw_stability	Cnr.	yaw_stability = 1.0  yaw_stability=1.000
elevator_trim_effectiveness	Cmdetr.	elevator_trim_effectiveness = 1.0  elevator_trim_effectiveness=1.000
aileron_trim_effectiveness	Cldatr.	aileron_trim_effectiveness = 1.0  aileron_trim_effectiveness=1.000
rudder_trim_effectiveness	Cndrtr.	rudder_trim_effectiveness = 1.0  rudder_trim_effectiveness=1.000
hi_alpha_on_roll	See notes above.
hi_alpha_on_yaw
p_factor_on_yaw	See notes above.	p_factor_on_yaw = 0.5  p_factor_on_yaw = 0.3
torque_on_roll		torque_on_roll = 1.0  torque_on_roll = 0.5  torque_on_roll = 0.3
gyro_precession_on_yaw	See notes above.	gyro_precession_on_yaw = 1.0  gyro_precession_on_yaw = 0.3
gyro_precession_on_pitch		gyro_precession_on_pitch = 1.0  gyro_precession_on_pitch = 0.3

[generalenginedata]

Every type of aircraft, even a glider, should have thissection in the aircraft.cfg file.  Basically, this sectiondescribes the type of engine, the number of engines, where the enginesare located, and a fuel flow scalar to modify how much fuel the enginerequires to produce the calculated power.

Property	Description	Examples
engine_type	Integer that identifies what type of engine is on theaircraft. 0 = piston, 1 = Jet, 2 = None, 3 = Helo-turbine, 4 = Rocket(not supported) 5 = Turboprop.	engine_type = 1  engine_type= 0  engine_type = 0  engine_type = 5
engine.0 to engine.n	Offset of the engine from the datum reference point. Each engine locationspecified increases the engine count (maximum of four engines allowed).	Engine.0 = 4.75, -16.1, -4.5  Engine.0= -3.000, 0.000, 2.000  Engine.0 = -1.4, -5.3, 0.0  Engine.0 = -107.5, -69.5, -6.9  Engine.1 = -76.0, -38.9, -10.4  Engine.2 = -76.0, 38.9, -10.4  Engine.3 = -107.5, 69.5, -6.9
fuel_flow_scalar	Scalar for modifying the fuel flow required by theengine(s). A value of less than 1.0 causes a slower fuel consumptionfor a given power setting, a value greater than 1.0 causes the aircraftto burn more fuel for a given power setting.	fuel_flow_scalar = 1  fuel_flow_scalar= 1.000  fuel_flow_scalar = 1.0  fuel_flow_scalar= 0.9
min_throttle_limit	Defines the minimum throttle position (percent of max).Normally 0 for piston aircraft and -0.25 for turbine airplane engineswith reverse thrust.	min_throttle_limit = -0.25  min_throttle_limit=0.000000  min_throttle_limit = -0.25;  min_throttle_limit = 0.0;
max_contrail_temperature	Ambient temperature, in celsius, in which engine vaporcontrails will turn on. The default value is about -39 degrees celsiusfor turbine engines. For piston engines, the contrail effect is turnedoff unless a temperature value is set here.	max_contrail_temperature = -30
master_ignition_switch	1=Available, 0=Not Available (default). If available,this switch must be on for the ignition circuit, and thus the engines,to be operable. Turning it off will stop all engines.	master_ignition_switch = 1
starter_type	Setto 1 for a Manual Starter	starter_type = 1
thrustanglepitchheading.0	Thrust pitch and heading angles in degrees ( positive pitch down, positive heading right).	ThrustAnglePitchHeading.0 = 0,0

[turbineenginedata]

A turbine engine ignites fuel and compressed air to createthrust.  These parameters define the power (thrust) output ofa given jet turbine engine.

Property	Description	Examples
fuel_flow_gain	Fuel flow gain constant.	fuel_flow_gain = 0.002  fuel_flow_gain = 0.002  fuel_flow_gain = 0.011  fuel_flow_gain = 0.0025
inlet_area	Engine nacelle inlet area, (in square feet).	inlet_area = 19.6  inlet_area = 60.0  inlet_area = 1.0  inlet_area = 9.4
rated_n2_rpm	Second stage compressor rated rpm.	rated_N2_rpm = 29920  rated_N2_rpm = 29920  rated_N2_rpm = 33000
static_thrust	Maximum rated static thrust at sea level (lbs).	static_thrust = 23500  static_thrust = 56750  static_thrust = 158  static_thrust = 12670
afterburner_available       afterburner_available	Boolean value to indicate if an afterburner is available; 0 = FALSE, 1 = TRUE.   This has been extended to take a number, indicating the number of afterburner stages available.	afterburner_available = 0  afterburner_available = 6
reverser_available	Specifies the scalar on the calculated reverse thrust effect. A value of 0 will cause no reverse thrust to be available. A value of 1.0 will cause the theoretical normal reverse thrust to be available. Other values will scale the normal calculated value accordingly.	reverser_available = 1  reverser_available = 0
thrustspecificfuelconsumption	Jet thrust specific fuel consumption. The ratio of fuel used in pounds per hour, to thrust in pounds. Applies at all speeds.	ThrustSpecificFuelConsumption = 0.6  ThrustSpecificFuelConsumption = 0.4
afterburnthrustspecificfuelconsumption	Jet thrust specific fuel consumption. The ratio of fuel used in pounds per hour, to thrust in pounds. Applies only when the afterburner is active.	AfterBurnThrustSpecificFuelConsumption = 0 AfterBurnThrustSpecificFuelConsumption = 0.5
afterburner_throttle_threshold	Percentage of throttle range when the afterburner engages.	afterburner_throttle_threshold = 0.76

[jet_engine]

The thrust_scalar parameter scales the calculated thrust for jetengines (thrust taken from the[TurbineEngineData] section).

Property	Description	Examples
thrust_scalar	Parameter that scales the calculated thrust provided bythe propeller.	thrust_scalar = 1.0

[electrical]

These parameters configure the characteristics of theaircraft's electrical system and its components. Each aircraft has abattery as well as an alternator or generator for each engine.

Below is a table of electrical section parameters shownwith default values for Bus Type, Max Amp Load and Min Voltage(the values applied if the parameters areomitted). The default Min Voltage equals 0.7*Max Battery Voltage. Thelist of components also reflects all of the systems currently linked tothe electrical system. If a component is included in the list but theaircraft does not actually have that system, the component is simplyignored.

Bus Type

Specifies which bus in the electrical system the component isconnected to, according to the following bus type codes:

Bus Type	Bus
0	MainBus (most components connected here)
1	AvionicsBus
2	BatteryBus
3	HotBattery Bus (bypasses Master switch)
4	Generator/AlternatorBus 1 (function of engine 1)
5	Generator/AlternatorBus 2 (function of engine 2)
6	Generator/AlternatorBus 3 (function of engine 3)
7	Generator/AlternatorBus 4 (function of engine 4)

Max Amp Load

Max Amp Load is the current required to power thecomponent, and of course becomes the additional load on the electricalsystem.

Min Voltage

Min Voltage is the minimum voltage required from thespecified bus for the component to function.

 

Property	Description	Examples
flap_motor	Bus type, max amp, min voltage	flap_motor = 0, 5 , 17.0
gear_motor	Bus type, max amp, min voltage	gear_motor = 0, 5 , 17.0
autopilot	Bus type, max amp, min voltage	autopilot = 0, 5 , 17.0
avionics_bus	Bus type, max amp, min voltage	avionics_bus = 0, 5, 17.0  avionics_bus = 0, 5 , 17.0  avionics_bus = 0, 5 , 9.5
avionics	Bus type, max amp, min voltage	avionics = 1, 5 , 17.0  avionics = 1, 5 , 9.5
pitot_heat	Bus type, max amp, min voltage	pitot_heat = 0, 2 , 17.0
additional_system	Bus type, max amp, min voltage	additional_system = 0, 2, 17.0  additional_system = 0, 2 , 17.0  additional_system = 0, 2 , 9.5
marker_beacon	Bus type, max amp, min voltage	marker_beacon = 1, 2 , 17.0  marker_beacon = 1, 2 , 9.0
gear_warning	Bus type, max amp, min voltage	gear_warning = 0, 2 , 17.0
fuel_pump	Bus type, max amp, min voltage	fuel_pump = 0, 5 , 17.0  fuel_pump = 0, 5 , 9.0
starter1	Bus type, max amp, min voltage	starter1 = 0, 20, 17.0
starter2	Bustype, max amp, min voltage
starter3	Bustype, max amp, min voltage
starter4	Bustype, max amp, min voltage
light_nav	Bus type, max amp, min voltage	light_nav = 0, 5 , 17.0
light_beacon	Bus type, max amp, min voltage	light_beacon = 0, 5 , 17.0
light_landing	Bus type, max amp, min voltage	light_landing = 0, 5 , 17.0
light_taxi	Bus type, max amp, min voltage	light_taxi = 0, 5 , 17.0
light_strobe	Bus type, max amp, min voltage	light_strobe = 0, 5 , 17.0
light_panel	Bus type, max amp, min voltage	light_panel = 0, 5 , 17.0
light_cabin	Bustype, max amp, min voltage
prop_sync	Bustype, max amp, min voltage
auto_feather	Bustype, max amp, min voltage
auto_brakes	Bustype, max amp, min voltage
standby_vacuum	Bustype, max amp, min voltage
hydraulic_pump	Bustype, max amp, min voltage
fuel_transfer_pump	Bustype, max amp, min voltage
propeller_deice	Bustype, max amp, min voltage
light_recognition	Bustype, max amp, min voltage
light_wing	Bustype, max amp, min voltage
light_logo	Bustype, max amp, min voltage
directional_gyro	Bustype, max amp, min voltage
directional_gyro_slaving	Bustype, max amp, min voltage
max_battery_voltage	The maximum voltage to which the battery can becharged.It is also the voltage available from the battery when the aircraft isinitialized. The battery voltage will decrease from this if thegenerators or alternators are not supplying enough current to meet thedemand of the active components.	max_battery_voltage = 24.0  max_battery_voltage = 24  max_battery_voltage = 12.0
generator_alternator_voltage	Voltage of the generators or alternators.	generator_alternator_voltage= 28.0  generator_alternator_voltage = 25.0  generator_alternator_voltage = 28  generator_alternator_voltage = 25
max_generator_alternator_amps	Maximum generator/alternator amps.	max_generator_alternator_amps= 60.0  max_generator_alternator_amps = 40.0  max_generator_alternator_amps = 50  max_generator_alternator_amps = 100
engine_generator_map	Listof flags, corresponding to the number of engines, indicating whetherthere is a generator configured with the engine.	engine_generator_map= 0,1,0
electric_always_available	Setto 1 if electric power is available regardless of the state of thebattery or circuit.

[contact_points]

You can configure and adjust the way aircraft reacts todifferent kinds of contact, including landing gear contact andarticulation, braking, steering, and damage accrued through excessivespeed. You can also configure each contact point independentlyforeach aircraft, and there is no limit to the number of points you canadd. When importing anaircraft that does not contain this set of data, the program willgenerate the data from the .air file the first time the aircraft isloaded, and then write it to the aircraft.cfg.

Each contact point contains a series of values that define thecharacteristics of the point, separated by commas. A contact point has16 parameters, described in the following table:

 

Contact Point Parameter (andexample)	Element	Description
1  (1)	Class	Integer defining the type of contact point: 0 = None, 1= Wheel, 2 = Scrape, 3 = Skid, 4 = Float, 5 = Water Rudder
2 (-18.0)	Longitudinal Position	The longitudinal distance of the point from the datum reference point.
3 (0)	Lateral Position	The lateral distance of the point from the datum reference point.
4 (-3.35)	Vertical Position	The vertical distance of the point from the datum reference point.
5 (3200)	Impact Damage Threshold	The speed at which an impact with the ground can causedamage (feet/min).
6 (0)	Brake Map	Defines which brake input drives the brake (wheelsonly). 0 = None, 1 = Left Brake, 2 = Right Brake.
7 (0.50)	Wheel Radius	Radius of the wheel (feet).
8 (180)	Steering Angle	The maximum angle (positive and negative) that a wheelcan pivot (degrees).
9 (0.25)	Static Compression	This is the distance a landing gear is compressed whentheempty aircraft is at rest on the ground (feet). This term defines the“strength” of the strut, where a smaller numberwillincrease the “stiffness” of the strut.
10 (2.5)	Ratio of Maximum Compression to Static Compression	Ratio of the max dynamic compression available in thestrutto the static value. Can be useful in coordinating the“compression” of the strut when landing.
11 (0.90)	Damping Ratio	This ratio describes how well the ground reactionoscillations are damped. A value of 1.0 is considered criticallydamped, meaning there will be little or no osciallation. A dampingratio of 0.0 is considered undamped, meaning that the oscillations willcontinue with a constant magnitude. Negative values result in anunstable ground handling situation, and values greater than 1.0 mightalso cause instabilities by being “over” damped.Typicalvalues range from 0.6 to 0.95.
12 (1.0)	Extension Time	The amount of time it takes the landing gear to fullyextendunder normal conditions (seconds). A value of zero indicates a fixedgear.
13 (4.0)	Retraction Time	The amount of time it takes the landing gear to fullyretractunder normal conditions (seconds). A value of zero indicates a fixedgear.
14 (0)	Sound Type	This integer value will map a point to a type of sound:
		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.
15 (0)	Airspeed Limit	This is the speed at which landing gear extensionbecomesinhibited (knots). Not used for scrape points or non-retractable gear.
16 (200)	Damage from Airspeed	The speed above which the landing gear accrues damage(knots). Not used for scrape points or non-retractable gear.

 

Each contact point's dataset takes the form “point.n=”, where“n” is the index to the particular point, followedby the data.

 

Property	Description	Examples
point.0 to point.n	Contact points that match the format described above.	point.0=1, 40.00, 0.00, -8.40,1181.1, 0, 1.442, 55.92, 0.6, 2.5, 0.9, 4.0, 4.0, 0, 220.0, 250.0  point.0= 1.000, 2.583, 0.000, -1.000,1574.803, 0.000, 0.504, 31.860, 0.235, 2.500, 0.731, 0.000, 0.000,0.000, 0.000, 0.000  point.0 = 1, 0.82, 0.00, -3.77, 1600, 0,0.633, 40, 0.42, 4.0, 0.90, 3.0, 3.0, 0, 152, 180  point.0 = 1, -25.0, 0.0, -17.5, 1000.0, 0,2.0, 70.0, 0.5, 3.5, 0.900, 9.0, 8.0, 0, 220, 250  point.1 = 1, -114.0, -18.0, -21.3, 2000.0, 1,2.0, 13.0, 3.0, 2.5, 0.900, 11.0, 9.0, 2, 220, 250  point.2 = 1, -114.0, 18.0, -21.3, 2000.0, 2,2.0, 13.0, 3.0, 2.5, 0.900, 11.0, 9.0, 3, 220, 250  point.3 = 2, -152.6, -103.5, 3.0, 700.0, 0,0.0, 0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 5, 0, 0  point.4 = 2, -152.6, 103.5, 3.0, 700.0, 0,0.0, 0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 6, 0, 0  point.5 = 2, 3.0, 0.0, 0.0, 700.0, 0, 0.0,0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 9, 0, 0  point.6 = 2, -222.7, 0.0, 4.0, 700.0, 0, 0.0,0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 4, 0, 0
max_number_of_points	Integer value indicating the maximum number of contactpointsthe program will look for.	max_number_of_points = 21
static_pitch	The static pitch of the aircraft when at rest on theground (degrees). The program uses this value to position the aircraftat startup, in slew, and at any other time when the simulation is notactively running.	static_pitch=0.04 static_pitch= 0.000  static_pitch = -1.5  static_pitch = 1.56
static_cg_height	The static height of the aircraft when at rest on theground (feet). The program uses this value to position the aircraft atstartup, in slew, and at any other time when the simulation is notactively running.	static_cg_height=7.67  static_cg_height= 1.000  static_cg_height = 18.6  static_cg_height = 3.43
gear_system_type	This parameter defines the system type which drives thegear extension and retraction. 0 = electrical 1 = hydraulic 2 = pneumatic 3 = manual 4 = none	gear_system_type=1  gear_system_type=0  gear_system_type=3
emergency_extension_type	One of: None=0,Pump=1,Gravity=2.	emergency_extension_type=2
tailwheel_lock	Boolean defining if a tailwheel lock is available(applicable only on tailwheel airplanes).	tailwheel_lock = 1

[gear_warning_system]

The following parameters define the functionality of theaircraft’s gearwarning system.  Thisis generally afunction of the throttle lever position and the flap deflection. 

Property	Description	Examples
gear_warning_available	Sets the type of gear warning system available on theaircraft, one of: 0 = None, 1 = Normal, 2 = Amphibian (audible alert for watervs. land setting).	gear_warning_available = 1
pct_throttle_limit	The throttle limit, below which the gear warning willactivate if the gear is not down and locked while the flaps aredeflected to at least the setting for flap_limit_idle below. This flaplimit can be 0 so that the warning effectively is a function of thethrottle. A value between: 0 (idle) and 1.0 (Max throttle).	pct_throttle_limit = 0.1
flap_limit_idle	In conjunction with the throttle limit specified above,this limit is the flap deflection, above which the warning willactivate if the gear is not down and locked while the throttle is belowthe limit specified above. By setting this limit to a value greaterthan zero, the pilot can reduce the throttle to idle without activatingthe warning. This is often utilized in jets to decelerate/descend theaircraft.	flap_limit_idle = 5.0  flap_limit_idle = 0.0  flap_limit_idle = 15.0
flap_limit_power	The flap limit, above which the warning will activate(regardless of throttle position).	flap_limit_power = 25.5flap_limit_power = 31.5 flap_limit_power = 30.0 flap_limit_power = 16.0

[brakes]

The following parameters define the aircraft's braking system:

 

Property	Description	Examples
parking_brake	Boolean setting if a parking brake is available on theaircraft.	parking_brake = 1  parking_brake=1  parking_brake = 0
toe_brakes_scale	Sets the scaling of the braking effectiveness. 1.0 isthe default. 0.0 scales the brakes to no effectiveness.	toe_brakes_scale = 0.885  toe_brakes_scale=1.000031  toe_brakes_scale = 1.24  toe_brakes_scale = 1.0
auto_brakes	The number of increments that the auto-braking switch can be turned to.	auto_brakes = 3  auto_brakes = 4  auto_brakes = 0
hydraulic_system_scalar	The ratio of hydraulic system pressure to maximum brakehydraulic pressure.	hydraulic_system_scalar = 1
differential_braking_scale	Differential braking is a function of the normal bothbrakes on and the rudder pedal input. The amount of difference betweenthe left and right brake is scaled by this value. 1.0 is the normalsetting if differential braking is desired (particularly on tailwheelairplanes). 0.0 is the setting if no differential braking is desired.	differential_braking_scale = 1.0

[hydraulic_system]

The following parameters define the aircraft's hydraulic system:

 

Property	Description	Examples
normal_pressure	The normal operating pressure of the hydraulic system,in pounds per square inch.	normal_pressure = 3000.0  normal_pressure=0.000000  normal_pressure = 0.0  normal_pressure = 1000.0
electric_pumps	The number of electric hydraulic pumps the aircraft isconfigured with.	electric_pumps = 0  electric_pumps = 1
engine_map	This series of flags sets whether the correspondingengines of the aircraft are configured with hydraulic pumps. The flagscorrespond in order of the engines, starting with the left-most enginefirst and moving right. By default, all engines are equipped to drive ahydraulic pump.	engine_map = 1,1,0,0  engine_map = 1,1,1,1  engine_map = 1,0,0,0  engine_map = 1

[views]

The following parameter define the pilot's viewpoint.

 

Property	Description	Examples
eyepoint	Position relative to datum reference point.	eyepoint=48.2, -1.35, 1.7  eyepoint=-0.205052,0.000000,3.604314  eyepoint = -18.55, -1.97, 10.7  eyepoint = -8.213, -0.8612, 2.220
zoom	Zoomthe view in or out from the viewpoint.	zoom=1.0

[flaps.n]

For each flap set that is on the aircraft, a corresponding [flaps.n] section should exist.  Most general aviation aircraft and smaller jets only have one set of flaps (trailing edge), but it is typical for the larger commercial aircraft to have a set of leading edge flaps in addition to the trailing edge flaps.  The number of flap sets are determined by the number of [flaps.n] sectionscontained in the aircraft.cfg file.

Property	Description	Examples
type	Integer value that indicates if this is a leading edgeor trailing edge flap set: 0 = no flaps 1 = trailing edge, 2 = leading edge.	type = 1  type=0  type = 2  type=1
span-outboard	The percentage of half-wing span the flap extends to(from the wing-fuselage intersection).	span-outboard = 0.8  span-outboard=0.500000  span-outboard = 0.41  span-outboard = 0.5
extending-time	Time it takes for the flap set to extend to the fullestdeflection angle specified (seconds).	extending-time = 20  extending-time=0.000000  extending-time = 2  extending-time = 25
flaps-position.0 to flaps-position.n	Each element of the flaps-position array indicates thedeflection angle to which the flaps will deflect (in degrees). Thelargestdeflection angle will be the one used for full flap deflection.	flaps-position.0= 0  flaps-position.0 = -9.0  flaps-position.0 = -7  flaps-position.0 = 0  flaps-position.1 = 1  flaps-position.2 = 2 flaps-position.3 = 5  flaps-position.4 = 10  flaps-position.5 = 15  flaps-position.6 = 25  flaps-position.7 = 30  flaps-position.8 = 40
damaging-speed	Speed at which the flaps begin to accrue damage (KnotsIndicated Airspeed, KIAS).	damaging-speed = 250  damaging-speed = 200  damaging-speed = 152  damaging-speed = 120
blowout-speed	Speed at which the flaps depart the aircraft (KnotsIndicated Airspeed, KIAS).	blowout-speed = 300  blowout-speed = 250  blowout-speed = 150  blowout-speed = 175
lift_scalar	The percentage of total lift due to flap deflectionthat this flap set is responsible for at full deflection.	lift_scalar = 1.0  lift_scalar = 0.7
drag_scalar	The percentage of total drag due to flap deflectionthat this flap set is responsible for at full deflection.	drag_scalar = 1.0  drag_scalar = 0.9
pitch_scalar	The percentage of total pitch due to flap deflectionthat this flap set is responsible for at full deflection.	pitch_scalar= 1.0  pitch_scalar= 0.9
system_type	Integer value that indicates what type of system drivesthe flaps to deflect:, one of: 0 = Electric 1 = Hydraulic 2 = Pneumatic 3 = Manual 4 = None	system_type = 1  system_type=0  system_type = 0  system_type = 3

[radios]

There should be a radio section in eachaircraft.cfg.  This section configures the radios for eachindividual aircraft.  Each of the following keywords has aflag or set of flags, that determine if the particular radio element isavailablein the aircraft.  A “1” is used for true(or available), and 0 for false (or not available). 

Property	Description	Examples
audio.1	Is there an audio panel, set to 1.	Audio.1 = 1  Audio.1 = 0
com.1	Two flags, set the first one to 1 if a Com1radio is available, and the second if it supports a standbyfrequency.	Com.1 = 1, 1  Com.1 = 1, 0
com.2	Two flags, set the first one to 1 if a Com2radio is available, and the second if it supports a standbyfrequency. You cannot have Com2 without Com1.	Com.2 = 1, 1  Com.2 = 1, 0
nav.1	Three flags, set the first to 1 if there is aNav1 receiver, the second if it supports a standbyfrequency, and the third if it supports a glideslope indication.	Nav.1 = 1, 1, 1  Nav.1 = 1, 0, 1  Nav.1 = 0, 0, 0
nav.2	Three flags, set the first to 1 if there is aNav2 receiver, the second if it supports a standbyfrequency, and the third if it supports a glideslopeindication. Youcannot have Nav2 without Nav1.	Nav.2 = 1, 1, 0  Nav.2 = 1, 0, 0
adf.1	If there is an ADF receiver, set to 1.	Adf.1 = 1  Adf.1 = 0
adf.2	Ifthere is an ADF2 receiver, set to 1.	Adf.2 = 1
transponder.1	If there is a transponder, set to 1.	Transponder.1 = 1  Transponder.1 = 0
marker.1	If there is a marker beacon receiver, set to 1.	Marker.1 = 1  Marker.1 = 0

[lights]

Eachlight that requires a special effect shouldbe entered in this section. The following table gives the codes for theswitches that will turn on the lights.

 

Code	Switch
1	Beacon
2	Strobe
3	Navigation or Position
4	Cockpit
5	Landing
6	Taxi
7	Recognition
8	Wing
9	Logo
10	Cabin

Property	Description	Examples
light.0 to light.n	The firstentry of the line defines which circuit, or switch, the light isconnectedto (see the code table above).  Multiplelights may be connected to a singleswitch.  The nextthree entries are theposition relative to datum reference point. The final entry is thespecial effect filename that is triggered (for example, fx_navred).  These files have .fx extensions and should be placedinthe Flight Sim World/effects folder.	light.0 = 3, -19.14, -47.24,1.38, fx_navredm ,  light.0 = 3, -150.30, -102.56, 3.22,fx_navredh ,  light.0 = 3, -6.60, -19.29, 0.79, fx_navred ,  light.0 = 3, 0.56, -28.41, 1.97,fx_navred ,  light.1 = 3, 0.56, 28.41, 1.97, fx_navgre,  light.2 = 3, -31.20, 0.00, 9.09,fx_navwhi ,  light.3 = 2, 0.89, -28.48, 1.87,fx_strobe ,

[keyboard_response]

The aircraft flight controls can be manipulated by thekeyboard. Because flight controls naturally become more sensitive asairspeed increases, it can become quite difficult to control theaircraft via the keyboard at high speeds.  To address thisproblem, the amount a single keypress increments a flight control isdecreased by a factor of 1/2 at the first airspeed (in knots) listed onthe line for the control, and to 1/8 at the second airspeed, and to a scale interpolated from these values for allairspeeds in between. The example below showsthat an elevator will increment by one degree when the airspeed iszero, by ¾ of one degree at 50 knots, ½of one degree at 100 knots, 5/16 of one degree at 140 knots, and 1/8 ofone degree at 180 knots or greater speed.

 

Property	Description	Examples
elevator	Two breakpoint speeds for keypress increments.	elevator = 150, 250  elevator=150.000000,250.000000  elevator = 100, 180  elevator = 160, 360
aileron	Two breakpoint speeds for keypress increments.	aileron = 150, 250  aileron=150.000000,250.000000  aileron = 200, 1000  aileron = 160, 360
rudder	Two breakpoint speeds for keypress increments.	rudder = 150, 250  rudder=150.000000,250.000000  rudder = 200, 1000  rudder = 160, 360

[direction_indicators]

This section is used to define the characteristics of the directionindicators on the instrument panels, but does not include themagnetic compass (which has a separate section).  The list ofindicators should be listed inorder: 0,1,2,…n. 

Property	Description	Examples
direction_indicator.0 to direction_indicator.n	One or two codes. If the indicator is type 4, thenthere must be two entries here (the indicator, and the indicator towhich this one is slaved).  The indicator codes are: 0 = None 1 = Vacuum gyro 2 = Electric gyro 3 = Electro-mag slaved compass 4 = Slaved to another indicator	direction_indicator.0=3,0  direction_indicator.0 = 0  direction_indicator.0=1,0  direction_indicator.0=0,0  direction_indicator.1=2,0
induction_compass.0 to induction_compass.n	Ifthere is an induction compass, one of: 1 = Electric 2 = Anemometer driven	induction_compass.0=2

[attitude_indicators]

This section is used to define the characteristics of the attitude indicators on the instrument panels. The list of indicators should belisted in order: 0,1,2,...n. 

Property	Description	Examples
attitude_indicator.0 to attitude_indicator.n	The system which drives the attitude indicator. One of: 0 = none 1 = Vacuum driven gyro 2 = Electrically driven gyro	attitude_indicator.0 = 2  attitude_indicator.0=1  attitude_indicator.0 = 1  attitude_indicator.0 = 0  attitude_indicator.1 = 1  attitude_indicator.1 = 2

 

[altimeters]

Property	Description	Examples
altimeter.0 to altimeter.n	If the parameter is set to 1, a separate altimeter is instantiated, which will operate independently of other altimeters, and can have failures applied to it.	altimeter.0=1  altimeter.0 = 1 altimeter.1=1  altimeter.1 = 1

 

[turn_indicators]

This section is used to define the characteristics of the turnindicators on the instrument panels.  The list of indicatorsshould be listed in order: 0,1,2,…n. 

Property	Description	Examples
turn_indicator.0	Two code values, which define the system on which theturn indicators are dependant. The first value is for turn,the second for bank. The codes are: 0 = None 1 = Electrically driven gyro 2 = Vacuum driven gyro	turn_indicator.0=0,0  turn_indicator.0=1,0  turn_indicator.0=1,1  turn_indicator.0=1

[vacuum_system]

The following parameters define the aircraft's vacuum system:

 

Property	Description	Examples
max_pressure	Maximum pressure in psi.	max_pressure=5.15  max_pressure=5.000000  max_pressure=5.150000  max_pressure=0
vacuum_type	Vacuum type, one of: 0 = None 1 = Engine pump (default) 2 = Pneumatic 3 = Venturi.	vacuum_type=2  vacuum_type=1  vacuum_type=0
electric_backup_pressure	Backup pressure in psi.	electric_backup_pressure=0.000000  electric_backup_pressure=4.900000  electric_backup_pressure=4.9  electric_backup_pressure=5.15
engine_map	This series of flags sets whether the correspondingengines of the aircraft are configured with vacuum systems. The flagscorrespond in order of the engines, starting with the left-most enginefirst and moving right.	engine_map=1,1  engine_map=1

[pneumatic_system]

The following parameters define the aircraft's pneumatic pressure system:

 

Property	Description	Examples
max_pressure	The maximum pressure of the pneumatic system.	max_pressure=18.000000  max_pressure=0.000000  max_pressure = 21.5  max_pressure=0
bleed_air_scalar	The ratio of bleed-air pressure from the engines to pneumatic air pressure in the pneumatic system.	bleed_air_scalar=1.000000  bleed_air_scalar=0.000000  bleed_air_scalar=0.00000  bleed_air_scalar=0.150000

[exits]

The following parameters define the aircraft's exits:

 

Property	Description	Examples
number_of_exits	This value defines the number of simulated exits, ordoors, on the aircraft.	number_of_exits = 3  number_of_exits =1  number_of_exits = 1  number_of_exits = 2
exit.0 to exit.n	Five values: the open and close rate percent per second(where 1.0 is fully open), the position relative to datum reference point, and the type ofexit, one of: 0 = Main 1 = Cargo 2 = Emergency	exit.0 = 0.4, 40.50,-6.0, 7.0, 0  exit.0 = 0.4, 41.3, -6.0, 4.0, 0  exit.0 = 0.4, -30.30, -9.5, 1, 0  exit.0 = 0.4, -16.50, -4.5, 0.5, 0  exit.1 = 0.4, -74.00, -4.5, 0.5, 1  exit.2 = 0.4, -36.50, -2.5, -1.0, 1

[effects]

The effects section of the file refers to the visual effects that result from various systems or reactions of the aircraft. An effect file associated with a keyword in this section will be used when the corresponding action is triggered.  If no entry is made a default effect file will be used. The table below outlines the aircraft effects currently supported, though of course not all effects are supported on allaircraft.

Each entry can be followed by a 1 if the effect is to be run for a single iteration. Set this numberto zero or leave blank (the default), for the effect to continue as long as the respectiveaction is active.

Make an entry in the configuration file to replace any of these effects with a new one. Or to turn off the effect add an entry that references the fx_dummy effect (which does nothing).

Property	Description	Default	Single Iteration	Examples
wake	The wake effect name.	fx_wake	False	wake=fx_wake
water	The landing, taxiing or taking off from water effect.	fx_spray	False	water=fx_spray
waterspeed	Traveling at speed on the water.	fx_spray	False
dirt	Moving on dirt.	fx_tchdrt	False	dirt=fx_tchdrt
concrete	Moving on concrete.	fx_sparks	False	concrete=fx_sparks  concrete=fx_tchdwn_s
touchdown	The touchdown effect, which usually is followed by anoptional 1 to indicate the effect is to be run once only.	fx_tchdwn	True	touchdown=fx_tchdwn, 1  touchdown=fx_tchdwn_s, 1
contrail	Contrail effect, applies to jets flying above 29000ft.	fx_contrail_l	False
startup	Engine startup.	fx_engstrt	True	startup=fx_engstrt_jenny startup=fx_engstrt_cub
landrotorwash	Rotor wash. Helicopters only.	fx_rtr_lnd	False
waterrotorwash	Water rotor wash. Helicopters only.	fx_rtr_wtr	False
vaportrail_l	Left wing vapor trail.	fx_vaportrail_l	False
vaportrail_r	Right wing vapor trail.	fx_vaportrail_r	False
l_wingtipvortice	Left wingtip vortice (contrails off the wingtip, usually from a jet such as the F18).	fx_wingtipvortice_l	True
r_wingtipvortice	Right wingtip vortice.	fx_wingtipvortice_r	True
fueldump	Fuel dump active.	No default effect	False
EngineFire	Engine fire.	fx_engfire	False	EngineFire=fx_heliFire
EngineDamage	Engine damage.	fx_engsmoke	False
EngineOilLeak	Oil leak.	fx_OilLeak	False
SkidPavement	Skid on tarmac, leaves a mark.	fx_skidmark	False
SnowSkiTrack	Skid on snow.	No default effect	False	SnowTrack = fx_snowtrack
WheelSnowSpray	Taking off on snow.	fx_WheelSnowSpray	False	WheelSnowSpray = fx_WheelSnowSpray
WheelWetSpray	Taking off on wet runway.	fx_WheelWetSpray	False	WheelWetSpray = fx_WheelWetSpray
WetEngineWash	Similar to waterrotorwash, the effect a propeller has on wet terrain when flying below 20m.	fx_WetEngineWash	False
SnowEngineWash	Similar to waterrotorwash, the effect a propeller has on snow covered terrain, or when it is snowing, when flying below 20m.	fx_SnowEngineWash	False
WaterBallastDrain	Draining the water ballast, applies only to sailplanes.	fx_WaterBallastDrain	False
PistonFailure	One or more pistons failed.	fx_PistonFailure	True
windshield_rain_effect_available	Special case, set this to 0 to turn off the effect of rain on the windshield.			windshield_rain_effect_available = 0

[autopilot]

The following parameters determine the functionality of theaircraft’s autopilot system, including the flight director.

Navigation Modes:

The navigation and glideslope controllers utilize standardproportional/integral /derivative feedback controllers (PID). The integrator and derivative controllers have boundaries, which arethe maximum error from the controlled parameter in which these areactive.  It is not necessary to have all three componentsactive.  Setting the respective control constant to 0effectively disables that component, allowing PI or PD controllers tobe utilized. Navigation mode parameters begin with nav_ or gs_.

Property	Description	Examples
autopilot_available	Setting this flag to a 1 makes available an autopilot system on the aircraft.	autopilot_available=1  autopilot_available=0
flight_director_available	Setting this flag to a 1 makes available a flight director on the aircraft.	flight_director_available=1  flight_director_available=0
default_vertical_speed	The default vertical speed, in feet per second, that the autopilot will command when selecting a large altitude change.	default_vertical_speed=1800  default_vertical_speed = 1800.0  default_vertical_speed= 700.0  default_vertical_speed= 1800.0
autothrottle_available	Setting this flag to a 1 makes available an autothrottle system on the aircraft.	autothrottle_available = 1  autothrottle_available= 0
autothrottle_arming_required	Setting this flag to 1 will require that the autothrottle be armed prior to it being engaged. Setting it to zero allows the autothrottle to be engaged directly.	autothrottle_arming_required = 1  autothrottle_arming_required= 0
autothrottle_max_rpm	This sets the maximum engine speed, in percent, that the autothrottle will attempt to maintain.	autothrottle_max_rpm = 90  autothrottle_max_rpm = 90
autothrottle_takeoff_ga	Setting this flag to 1 enables takeoff / go-around operations with the autothrottle.	autothrottle_takeoff_ga = 1  autothrottle_takeoff_ga= 0
default_pitch_mode	This determines the default pitch mode when the autopilot logic is turned on. 0 = None 1 = Pitch Hold (current pitch angle) 2 = Altitude Hold (current altitude) If no value is set, Pitch Hold will be the default.
pitch_takeoff_ga	The default pitch that the Takeoff/Go-Around mode references.	pitch_takeoff_ga=8.0  pitch_takeoff_ga=0.0
max_pitch	The maximum pitch angle in degrees that the autopilot will command either up or down.	max_pitch=10.0
max_pitch_acceleration	The maximum angular pitch acceleration, in degrees per second squared, that the autopilot will command up or down.	max_pitch_acceleration=1.0
max_pitch_velocity_lo_alt	The maximum angular pitch velocity, in degrees per second, which the autopilot will command when at an altitude below that specified by the variable max_pitch_velocity_lo_alt_breakpoint.	max_pitch_velocity_lo_alt=2.0
max_pitch_velocity_hi_alt	The maximum angular pitch velocity, in degrees per second, which the autopilot will command when at an altitude above the altitude specified by the variable max_pitch_velocity_hi_alt_breakpoint. The maximum velocity is interpolated between the hi and lo altitude velocities when between the hi and lo altitude breakpoints.	max_pitch_velocity_hi_alt=1.5
max_pitch_velocity_lo_alt_breakpoint	The altitude below which the autopilot maximum pitch velocity is limited by the variable max_pitch_velocity_lo_alt.	max_pitch_velocity_lo_alt_breakpoint=20000.0
max_pitch_velocity_hi_alt_breakpoint	The altitude above which the autopilot maximum pitch velocity is limited by the variable max_pitch_velocity_hi_alt. The maximum velocity is interpolated between the hi and lo altitude velocities when between the hi and lo altitude breakpoints.	max_pitch_velocity_hi_alt_breakpoint=28000.0
max_bank	The maximum bank angle in degrees that the autopilot will command either left or right.	max_bank=25.0  max_bank=30,25,20,15,10  max_bank=30,15  max_bank=25.000000
max_bank_acceleration	The maximum angular bank acceleration, in degrees per second squared, that the autopilot will command left or right.	max_bank_acceleration=1.8
max_bank_velocity	The maximum angular bank velocity, in degrees per second, which the autopilot will command left or right.	max_bank_velocity=3.000000
max_throttle_rate	This value sets the maximum rate at which the autothrottle will move the throttle position. In the example, the maximum rate is set to 10% of the total throttle range per second.	max_throttle_rate=0.100000
nav_proportional_control	Proportional controller constant in lateral navigation modes.	nav_proportional_control=12.00  nav_proportional_control=16.00  nav_proportional_control=9.00  nav_proportional_control=11.00
nav_integrator_control	Integral controller constant in lateral navigation modes.	nav_integrator_control=0.25  nav_integrator_control=0.17  nav_integrator_control=0.20  nav_integrator_control=0.250000
nav_derivative_control	Derivative controller constant in lateral navigation modes.	nav_derivative_control=0.00  nav_derivative_control=0.000000
nav_integrator_boundary	The boundary, or maximum signal error, in degrees in which the integrator function is active. In the example, the integrator is active when the error is between -2.5 and +2.5 degrees from the centerline of the navigation signal.	nav_integrator_boundary=2.50
nav_derivative_boundary	The boundary, or maximum signal error, in degrees in which the derivative function is active. In the example, the derivative controller is not active because the maximum error is set to 0.	nav_derivative_boundary=0.00
gs_proportional_control	Proportional controller constant in glideslope mode.	gs_proportional_control=25.0  gs_proportional_control = 18.0  gs_proportional_control=9.52  gs_proportional_control=9.520000
gs_integrator_control	Integral controller constant in glideslope mode.	gs_integrator_control=0.53  gs_integrator_control = 0.33  gs_integrator_control=0.26  gs_integrator_control=0.260000
gs_derivative_control	Derivative controller constant in glideslope mode.	gs_derivative_control = 0.00
gs_integrator_boundary	The boundary, or maximum signal error, in degrees in which the glideslope integrator function is active. In the example, the integrator is active when the error is between -0.7 and +0.7 degrees from the centerline of the glideslope signal.	gs_integrator_boundary = 0.70
gs_derivative_boundary	The boundary, or maximum signal error, in degrees in which the derivative function is active. In the example, the derivative controller is not active because the maximum error is set to 0.	gs_derivative_boundary = 0.00
yaw_damper_gain	The proportional gain on the yaw dampers yaw rate error.	yaw_damper_gain = 1.0  yaw_damper_gain = 0.0
direction_indicator	Indicates which direction indicator system on the aircraft is being referenced by the autopilot. 0 = the first, and is the default.	direction_indicator=1
attitude_indicator	Indicates which attitude indicator system on the aircraft is being referenced by the autopilot. 0 = the first, and is the default.	attitude_indicator =1
default_bank_mode	This determines the default bank mode when the autopilot logic is turned on. 0 = None 1 = Wing Level Hold 2 = Heading Hold (current heading). If no value is set, Wing Level Hold will be the default.	default_bank_mode=2

[fuel]

This section defines the characteristics of the fuel system,including the tanks, fuel type, and the number of fuelselectors. The number of fuel selectors is intended to matchthe number of visualselectors on the instrument panel.

Property	Description	Examples
center1 center2 center3 leftmain leftaux lefttip rightmain rightaux righttip external1 external2	Position of the tank relative to datum reference point, followed by the usable and unusable capacities of the tanks, in gallons.	Center1 = -83.5, 0.0, -7.0,17164.0, 0.0  Center1 = -48.7, 0.0, -4.0, 982.0, 0.0  Center2 = -193.5, 0.0, 6.0,3300.0, 0.0  Center3=-10.600000,0.000000,-1.900000,25.000000,0.000000  LeftMain = -3, -19, 0, 1500, 0  RightMain = -8.46, 6.45, 0.0, 71.0, 0.0  LeftAux = -2.24, -11.4, 2.40, 15.0, 0.00
fuel_type	One of: 1 = Avgas 2 = JetA	fuel_type = 2  fuel_type = 1
number_of_tank_selectors	Number of fuel tank selectors (maximum 4 and should belessthan or equal to the number of engines).	number_of_tank_selectors=1  number_of_tank_selectors = 2
electric_pump	Boolean that sets whether an electric boost pump isavailable, 0 = FALSE, 1 = TRUE.	electric_pump=0  electric_pump = 1
fuel_dump_rate	Percent of fuel that can be dumped per second.	fuel_dump_rate = 0.0167
engine_driven_pump	Set to 0 if the pump is engine driven (1 is thedefault).	engine_driven_pump=0  engine_driven_pump=1
manual_pump	Set to 1 if there is a manual transfer pump.	manual_transfer_pump=1
anemometer_pump	Setto 1 if there is an anemometer pump.	anemometer_pump=1

 

 

[airplane_geometry]

This section has been added mainlyfor reference. Although you can editthese values by hand here in the aircraft.cfg file, modification ofsome of these variables will have little to no effect on airplaneperformance, as the flight model aerodynamic coefficients areall located in the .air file. 

Property	Description	Examples
wing_area	Area of the top surface of the entire wing tip-to-tip(ft2).	wing_area = 1137.0  wing_area= 150.000  wing_area = 5825.0  wing_area = 199.0
wing_span	Wing span is the horizontal distance from wing-tip towing-tip (feet).	wing_span = 94.75  wing_span= 30.000  wing_span = 211.4  wing_span = 37.8
wing_root_chord	Length of the wing chord (leading edge to trailingedge) at the intersection of the wing and the fuselage (feet).	wing_root_chord = 18.0  wing_root_chord= 5.000  wing_root_chord = 48.8  wing_root_chord = 5.3
wing_dihedral	When looking at the front of an aircraft, this is theangle between the wing leading edge and a horizontal line parallel tothe ground (degrees).	wing_dihedral = 6.2  wing_dihedral= 7.998  wing_dihedral = 7.0  wing_dihedral = 6.9
wing_incidence	When looking at the side of an aircraft from the wingtip, this is the angle the mean wing chord makes with a horizontal lineparallel to the ground, (degrees). Note: this parameter is not used inthe real-time aerodynamic calculations, as it is already factored intothe lift and drag parameters.	wing_incidence = 1.0  wing_incidence= 0.000  wing_incidence = 2.0  wing_incidence = 1.5
wing_twist	This is the difference in wing incidence from the rootchord and the tip chord of the wing, (degrees). Also known as wash-out.	wing_twist = -0.5  wing_twist= -1.000 wing_twist = -1.0  wing_twist = -1.5
oswald_efficiency_factor	This is a measure of the aerodynamic efficiency of thewing. A theoretically perfect wing will have a factor of 1.0.	oswald_efficiency_factor=0.750  oswald_efficiency_factor= 0.68  oswald_efficiency_factor= 0.7
wing_winglets_flag	Boolean to indicate if the aircraft incorporates theuse of winglets; 0 = FALSE, 1 = TRUE.	wing_winglets_flag= 0  wing_winglets_flag = 1
wing_sweep	When looking down on top of an aircraft, this is theangle the wing leading edge makes with a horizontal line perpendicularto the fuselage, (degrees).	wing_sweep = 25.0  wing_sweep = 37.5  wing_sweep = 0.0
wing_pos_apex_lon	Longitudinal distance of the wing apex (measured atcenterline of aircraft) from defined reference point (feet). Thisdistance is measured positive in the forward (out the aircraft nose)direction.	wing_pos_apex_lon = 8.0  wing_pos_apex_lon= 0.000  wing_pos_apex_lon = -58.2  wing_pos_apex_lon = -5.6
wing_pos_apex_vert	Vertical distance of the wing apex (measured atcenterline of aircraft) from defined reference point (feet). Thisdistance is measured positive in the up direction.	wing_pos_apex_vert = 0  wing_pos_apex_vert = -3.6
htail_area	Area of the top surface of the entire horizontal tail(tip-to-tip) (ft2).	htail_area = 338.0  htail_area= 28.000  htail_area = 1470  htail_area = 60.0
htail_span	Horizontal tail span is the horizontal distance fromhorizontal tail-tip to horizontal tail -tip (feet).	htail_span = 41.7  htail_span= 7.917  htail_span = 72.8  htail_span = 15.9
htail_pos_lon	Longitudinal distance of the horizontal tail apex(measured at centerline of aircraft) from defined reference point(feet). This distance is measured positive in the forward (out theaircraft nose) direction.	htail_pos_lon = -35.0  htail_pos_lon= -11.417  htail_pos_lon = -210.0  htail_pos_lon = -20.1
htail_pos_vert	Vertical distance of the horizontal tail apex (measuredat centerline of aircraft) from defined reference point, (feet). Thisdistance is measured positive in the up direction.	htail_pos_vert = 0.0  htail_pos_vert = 12.7  htail_pos_vert = 0.9
htail_incidence	When looking at the side of an aircraft from thehorizontal tail tip, this is the angle the mean horizontal tail chordmakes with a horizontal line parallel to the ground (degrees).	htail_incidence= 0.000  htail_incidence = 0.5  htail_incidence = 4.0
htail_sweep	When looking down on top of an aircraft, this is theangle the horizontal tail leading edge makes with a horizontal lineperpendicular to the fuselage (degrees).	htail_sweep = 30.0  htail_sweep = 37.5  htail_sweep = 0.0
vtail_area	Area of the surface of one side of the vertical tail(fuselage-to-tip) (ft2).	vtail_area = 224.0  vtail_area= 7.000  vtail_area = 1060  vtail_area = 88.0
vtail_span	Vertical tail span is the vertical distance from thevertical tail-fuselage intersection to the tip of the vertical tail(feet).	vtail_span = 20.0  vtail_span= 3.017  vtail_span = 37.1  vtail_span = 10.7
vtail_sweep	When looking at the side of the vertical tail, this isthe angle the vertical tail leading edge makes with a vertical lineperpendicular to the fuselage (degrees).	vtail_sweep = 35.0  vtail_sweep = 45.0  vtail_sweep = 0.0
vtail_pos_lon	Longitudinal distance of the vertical tail apex(measured at centerline of aircraft) from defined reference point,(feet). This distance is measured positive in the forward (out theaircraft nose) direction.	vtail_pos_lon = -35.8  vtail_pos_lon= -11.417  vtail_pos_lon = -198.5  vtail_pos_lon = -22.9
vtail_pos_vert	Vertical distance of the vertical tail apex (measuredat centerline of aircraft) from defined reference point (feet). Thisdistance is measured positive in the up direction.	vtail_pos_vert = 5.8  vtail_pos_vert= 1.500  vtail_pos_vert = 26.1  vtail_pos_vert = 3.1
elevator_area	Area of the top surface of the entire elevator(tip-to-tip) (ft2).	elevator_area = 70.5  elevator_area= 12.040  elevator_area = 327  elevator_area = 20.0
aileron_area	Area of the top surface of all the ailerons on the wing(ft2).	aileron_area = 26.9  aileron_area= 15.000  aileron_area = 225  aileron_area = 11.3
rudder_area	Area of the side surface of the entire rudder (ft2).	rudder_area = 56.2  rudder_area= 2.450  rudder_area = 230  rudder_area = 10.5
elevator_up_limit	Angular limit of the elevator when deflected up(degrees).	elevator_up_limit = 22.5  elevator_up_limit= 27.502  elevator_up_limit = 25  elevator_up_limit = 17.0
elevator_down_limit	Angular limit of the elevator when deflected down(degrees).	elevator_down_limit = 19.5  elevator_down_limit= 20.626  elevator_down_limit = 15  elevator_down_limit = 15.5
aileron_up_limit	Angular limit of the aileron when deflected up(degrees).	aileron_up_limit = 20.0  aileron_up_limit= 19.481  aileron_up_limit = 25  aileron_up_limit = 18.0
aileron_down_limit	Angular limit of the aileron when deflected down(degrees).	aileron_down_limit = 20.0  aileron_down_limit= 14.897  aileron_down_limit = 15  aileron_down_limit = 18.0
rudder_limit	Angular limit of the rudder deflection (degrees).	rudder_limit = 26.0  rudder_limit= 23.491  rudder_limit = 31.5 rudder_limit = 30.0
elevator_trim_limit	Angular limit of the elevator trim tab (degrees).	elevator_trim_limit = 20.0  elevator_trim_limit= 20.000  elevator_trim_limit = 20  elevator_trim_limit = 15.0
spoiler_limit	Angular limit of the wing spoilers on an aircraft,(degrees). If this limit is zero, no spoilers exist for the aircraft.	spoiler_limit = 60.0  spoiler_limit= 59.989  spoiler_limit = 45  spoiler_limit = 0.0
spoiler_extension_time	Spoiler extension time in seconds.	spoiler_extension_time = 2.0  spoiler_extension_time=5.000000  spoiler_extension_time = 0.2  spoiler_extension_time = 1.0
spoilerons_available	Boolean to indicate if the spoilers also behave asspoilerons for roll control (if spoilers are available): 0 = FALSE, 1 =TRUE.	spoilerons_available = 1 spoilerons_available= 0  spoilerons_available = 0
aileron_to_spoileron_gain	If spoilerons are available, this value is the constantused in determining the amount of spoiler deflection per ailerondeflection.	aileron_to_spoileron_gain = 3  aileron_to_spoileron_gain = 0  aileron_to_spoileron_gain = 4.6
min_ailerons_for_spoilerons	This value indicates at what aileron deflection thespoilers are become active for roll control, (degrees).	min_ailerons_for_spoilerons = 10  min_ailerons_for_spoilerons = 0  min_ailerons_for_spoilerons = 5
min_flaps_for_spoilerons	This value indicates at what minimum flap handleposition the spoilerons become active.	min_flaps_for_spoilerons=0.0
auto_spoiler_available	Set to 1 if auto spoiler is available.	auto_spoiler_available = 1  auto_spoiler_available = 0
positive_g_limit_flaps_up	Design g load tolerance (flaps up).	positive_g_limit_flaps_up = 4.0  positive_g_limit_flaps_up = 3.0  positive_g_limit_flaps_up = 5.5
positive_g_limit_flaps_down	Design g load tolerance (flaps down).	positive_g_limit_flaps_down= 3.0  positive_g_limit_flaps_down=2.000000  positive_g_limit_flaps_down= 5.5
negative_g_limit_flaps_up	Design g load tolerance (negative, flaps up).	negative_g_limit_flaps_up = -3.0  negative_g_limit_flaps_up = -2.0  negative_g_limit_flaps_up = -1.5
negative_g_limit_flaps_down	Design g load tolerance (negative, flaps down).	negative_g_limit_flaps_down= -2.0  negative_g_limit_flaps_down= -1.5  negative_g_limit_flaps_down= -3.5
load_safety_factor	Design g load safety factor.	load_safety_factor = 1.5
fly_by_wire	Fly by wire system available.	fly_by_wire = 1
spoiler_handle_available	Boolean that configures the airplane with manualcontrol of the spoiler deflections. 0 = FALSE, 1 = TRUE.	spoiler_handle_available= 0
flap_to_aileron_scale	Flaperons - deflection of ailerons due to flapdeflection.	flap_to_aileron_scale= 0.3  flap_to_aileron_scale = 0.5
aileron_to_rudder_scale	Linkthe rudder to aileron input.	aileron_to_rudder_scale = 0.4

[referencespeeds]

The values given in this section are mainly for reference, asthe performance of the aircraft is held in the .air file.

Property	Description	Examples
flaps_up_stall_speed	Stall speed of the aircraft in a clean (flaps up)configuration at standard sea level conditions, (Knots True Airspeed,KTAS).	flaps_up_stall_speed = 142.0  flaps_up_stall_speed= 24.000  flaps_up_stall_speed = 140.0  flaps_up_stall_speed = 84.0
full_flaps_stall_speed	Stall speed of the aircraft in a dirty (flaps fulldown) configuration at standard sea level conditions, (Knots TrueAirspeed, KTAS).	full_flaps_stall_speed = 113.0  full_flaps_stall_speed= 24.000  full_flaps_stall_speed = 112.0  full_flaps_stall_speed = 75.0
cruise_speed	Typical cruise speed of the aircraft in a clean (flapsup) configuration at a typical cruise altitude, (Knots True Airspeed,KTAS).	cruise_speed = 477.0  cruise_speed= 84.560  cruise_speed = 505.0  cruise_speed = 180.0
max_mach	Maximum design mach of the aircraft. This generallyonly applies to turbine airplanes.	max_mach = 0.82  max_mach = 0.92  max_mach = 0.58  max_mach = 0.83
max_indicated_speed	Maximum design indicated airspeed. Also referred to asNever Exceed Speed or Red Line of the aircraft, (Knots IndicatedAirspeed).	max_indicated_speed = 340  max_indicated_speed=65.000000  max_indicated_speed = 365.0  max_indicated_speed = 223

[forcefeedback]

As detailed in the tables below, the parameters in thissection of an aircraft.cfg file define the forces generated by thataircraft if the user is operating a force feedback joystick.

Stick shaker parameters

These parameters define the simulated stick shaker force felt in thestick or yoke when flying an aircraft equipped with a stick shaker.

Gear bump parameters

These parameters define the simulated forces transferred from theairframe and gear drag to the stick or yoke when theaircraft’s nose and main landing gear is raised or lowered(cycled). In fixed-gear aircraft this effect won't be felt because, bydefinition, the landing gear doesn't move. Different aircraft havedifferent gear geometries that result in each of the gear mechanismsstarting and ending its cycle at a different time. The timing deltasare brief, typically less than a second between the time that each gearstarts and ends its cycle.

Ground bumps parameters

These parameters collectively define a composite force that simulatesthe forces felt through an aircraft's ground steering controls as theaircraft travels over an uneven surface. The parameters are dividedinto two subgroups (numbered 1 and 2), and define the behavior of twodistinct forces. The combination of the two forces define acomposite force that is transferred to the stick or yoke. The twoforces are both sinusoidal periodic forces, with frequencies determinedby the following linear equation:

• frequency = (ground_bumps_slope * aircraft_ground_speed) +ground_bumps_intercept

The ground_bumps_magnitude parameters set the magnitude of the force.The ground_bumps_angle parameters set the direction from which theforce is felt.

Crash parameters

These parameters define the simulated forces felt in the stick or yokewhen the aircraft crashes. The parameters are divided into twosubgroups (numbered 1 and 2), and define the behavior of two distinctcrash-induced forces. The first force is a constant force that lastsfor 0.5 seconds. After 0.5 seconds, it stops and the second forcestarts. The second force is a periodic square wave force; its amplitudedeclines linearly to 0.

Property	Description	Examples
gear_bump_nose_magnitude	Integer from 0 - 10000.	gear_bump_nose_magnitude=3000  gear_bump_nose_magnitude=6000
gear_bump_nose_direction	Integer from 0 - 35999 degrees.	gear_bump_nose_direction=18000
gear_bump_nose_duration	Integer, microseconds.	gear_bump_nose_duration=250000
gear_bump_left_magnitude	Integer from 0 - 10000.	gear_bump_left_magnitude=2700  gear_bump_left_magnitude=6000
gear_bump_left_direction	Integer from 0 - 35999 degrees.	gear_bump_left_direction=35500  gear_bump_left_direction=9000
gear_bump_left_duration	Integer, microseconds.	gear_bump_left_duration=250000
gear_bump_right_magnitude	Integer from 0 - 10000.	gear_bump_right_magnitude=2700  gear_bump_right_magnitude=6000
gear_bump_right_direction	Integer from 0 - 35999 degrees.	gear_bump_right_direction=00500  gear_bump_right_direction=27000
gear_bump_right_duration	Integer, microseconds.	gear_bump_right_duration=250000
ground_bumps_magnitude1	Integer from 0 - 10000.	ground_bumps_magnitude1=1300  ground_bumps_magnitude1=3250  ground_bumps_magnitude1=2500  ground_bumps_magnitude1=2600
ground_bumps_angle1	Integer from 0 - 35999 degrees.	ground_bumps_angle1=8900
ground_bumps_intercept1	Floating point number, from 0 to 1,000,000 cyclesper second.	ground_bumps_intercept1=3.0  ground_bumps_intercept1=5.0  ground_bumps_intercept1=10.0  ground_bumps_intercept1=4.0
ground_bumps_slope1	Floating point number, from 0 to 1,000,000 cyclesper second.	ground_bumps_slope1=0.20  ground_bumps_slope1=0.48  ground_bumps_slope1=0.300  ground_bumps_slope1=0.6
ground_bumps_magnitude2	Integer from 0 - 10000.	ground_bumps_magnitude2=200  ground_bumps_magnitude2=750  ground_bumps_magnitude2=350  ground_bumps_magnitude2=1200
ground_bumps_angle2	0 - 35999 degrees.	ground_bumps_angle2=09100  ground_bumps_angle2=9100
ground_bumps_intercept2	Floating point number, from 0 to 1,000,000 cyclesper second.	ground_bumps_intercept2=1.075  ground_bumps_intercept2=0.075  ground_bumps_intercept2 =1.075  ground_bumps_intercept2=0.085
ground_bumps_slope2	Floating point number, from 0 to 1,000,000 cyclesper second.	ground_bumps_slope2=0.035  ground_bumps_slope2=1.0  ground_bumps_slope2=0.65
crash_magnitude1	Sets the magnitude of the first force, from 0 to 10000.	crash_magnitude1=10000
crash_direction1	Sets the direction from which first force is felt, from0 to 35999.	crash_direction1=01000
crash_magnitude2	Sets the initial magnitude of the second force, from 0to 10000.	crash_magnitude2=10000
crash_direction2	Sets the direction from which the second force is felt,from 0 to 35999.	crash_direction2=9000
crash_period2	Determines the frequency (frequency = 1/period) of thesecond crash force, in microseconds.	crash_period2=75000
crash_duration2	Sets the amount of time that the second crash force isfelt, in microseconds.	crash_duration2=2500000  crash_duration2=3500000
stick_shaker_magnitude	Integer from 0 - 10000.	stick_shaker_magnitude=5000
stick_shaker_direction	Integer from 0 - 35999 degrees.	stick_shaker_direction=0
stick_shaker_period	In microseconds.	stick_shaker_period=111111

[stall_warning]

This section defines the stall warning system of the aircraft.

 

Property	Description	Examples
type	This flag determines the type of stall warning system,one of: 0 = None 1 = Suction 2 = Electric	type=2  type=0  type=1
stick_shaker	Set to 1 if the aircraft has a stick shaker.	stick_shaker=1  stick_shaker=0

[deice_system]

This section defines the deice system of the aircraft.

 

Property	Description	Examples
structural_deice_type	Type of deicer, of one: 0 = None 1 = Heated Leading Edge 2 = Bleed Air Boots 3 = Eng Pump Boots.	structural_deice_type=1 structural_deice_type=0  structural_deice_type=3  structural_deice_type=2

[piston_engine]

A piston engine’s power can be determined through aseries of equations that represent the Otto cycleof a four-stroke piston engine, multiplied by the number of pistonsavailable.  This section contains all the information the simulation needs to be able to determine how much power theengines are capable of producing.  Power can also be scaled fromthecalculated values generated for piston engines with the“power_scalar” value.

Property	Description	Examples
detonation_onset	The manifold pressure that if reached or exceeded will lead to the engine detonating.	detonation_onset = 36  detonation_onset = 80
supercharged	On/off.	supercharged=1
supercharger_boost	Multiplier on manifold pressure if supercharger is engaged..	supercharger_boost=1.20
supercharger_power_cost	Percent of horsepower required to drive supercharger.	supercharger_power_cost=0.22
emergency_boost_duration	Emergency boost duration in seconds. The emergency boost system was designed to model the systems used on WWII aircraft. The nitrous and supercharging systems are available for more modern aircraft.	emergency_boost_duration=0
max_rpm_mechanical_efficiency_scalar	Scalar value that can be modified to tune themechanical efficiency of the engine at maximum rpm. Increase this valueto increase the mechanical efficiency, decrease it to decrease themechanical efficiency.	max_rpm_mechanical_efficiency_scalar=1.0
idle_rpm_mechanical_efficiency_scalar	Scalar value that can be modified to tune themechanical efficiency of the engine at idle rpm. Increase this value toincrease the mechanical efficiency, decrease it to decrease themechanical efficiency.	idle_rpm_mechanical_efficiency_scalar=1.0
max_rpm_friction_scalar	Scalar value that can be modified to tune the internalfriction of the engine at maximum rpm. Increase this value to increasethe friction, decrease it to decrease the friction.	max_rpm_friction_scalar=1.000
idle_rpm_friction_scalar	Scalar value that can be modified to tune the internalfriction of the engine at idle rpm. Increase this value to increase thefriction, decrease it to decrease the friction, (can be used to tunethe rpm at which the engine idles).	idle_rpm_friction_scalar=1.000
cylinder_displacement	Cubic inches per cylinder displacement.	cylinder_displacement=55.000  cylinder_displacement= 91.7  cylinder_displacement= 90.0  cylinder_displacement= 109.4
two_stroke_cycle	Two stroke engine.	two_stroke_cycle = 1
compression_ratio	Compression ratio of each cylinder.	compression_ratio= 11.500  compression_ratio= 8.0  compression_ratio= 8.5  compression_ratio= 6.0
number_of_cylinders	Integer value; number of cylinders in the engine.	number_of_cylinders= 2  number_of_cylinders= 6  number_of_cylinders=4  number_of_cylinders=9
max_rated_rpm	Maximum rated revolutions per minute (RPM) of theengine (red line).	max_rated_rpm= 5500.000  max_rated_rpm= 2700.0  max_rated_rpm= 2700  max_rated_rpm= 2300
max_rated_hp	Maximum rated brake horsepower output of the engine.	max_rated_hp= 53.600  max_rated_hp= 300.0  max_rated_hp= 180  max_rated_hp= 450
fuel_metering_type	Integer value indicating the fuel metering type, one of: 0 =Fuel Injected 1 = Gravity Carburetor, 2 = Aerobatic Carburetor.	fuel_metering_type= 1  fuel_metering_type= 0  fuel_metering_type = 1
cooling_type	Integer value indicating the method of engine cooling,one of: 0 = air cooled 1 = liquid cooled.	cooling_type= 1  cooling_type= 0
normalized_starter_torque	This value can be modified to increase/decrease thetorque supplied by the starter to get the prop turning. Increase thisvalue for a greater torque effect, decrease it for a lower torquesetting.	normalized_starter_torque= 0.3
turbocharged	Boolean to indicate if the engine is turbocharged; 0 =FALSE, 1 = TRUE.	turbocharged= 0  turbocharged= 1
max_design_mp	If a turbocharger is present, this value indicates themaximum design manifold pressure supplied by the turbocharger (inHg).	max_design_mp= 0.0  max_design_mp= 36.5
min_design_mp	If a turbocharger is present, this value indicates theminimum design manifold pressure of the turbocharger (inHg).	min_design_mp= 1.0  min_design_mp= 10
critical_altitude	Altitude to which the turbocharger, if present, willprovide the maximum design manifold pressure (feet).	critical_altitude= 0.0  critical_altitude= 5000
emergency_boost_type	Integer value indicating the emergency boost typeavailable, one of: 0 = None 1 = Water Injection 2 = Methanol/Water Injection 3 = War Emergency Power, (typically used in WWII combat aircraft).	emergency_boost_type= 0
emergency_boost_mp_offset	Additional manifold pressure supplied by emergencyboost, if available.	emergency_boost_mp_offset=0.000
emergency_boost_gain_offset	Multiplier on manifold pressure due to emergency boost.	emergency_boost_gain_offset=0.000
fuel_air_auto_mixture	Boolean to indicate if automatic fuel-to-air mixture isavailable; 0 = FALSE, 1 = TRUE.	fuel_air_auto_mixture= 0
auto_ignition	Boolean to indicate if automatic ignition is available;0 = FALSE, 1 = TRUE.	auto_ignition= 0
power_scalar	Changing this value affects the amount of powerdelivered by the engine to the propellor shaft.	power_scalar = 1.0
bestpowerspecificfuelconsumption	Specific fuel consumption at Best Power mixture ratio.	BestPowerSpecificFuelConsumption=0.49
magneto_order_left_right_both	Sets the order of the magneto switch direction.	magneto_order_left_right_both =1
number_of_magnetos	Numberof magnetos.	number_of_magnetos = 1

[propeller]

The thrust generated by a given propeller is a function of thepower delivered through the propeller shaft, rpm, blade angle, airplanespeed, and ambient density.

Property	Description	Examples
propeller_type	Integer that identifies what type of propeller is onthe aircraft, one of: 0 = Constant Speed 1 = Fixed Pitch.	propeller_type= 1  propeller_type= 0  propeller_type = 0
propeller_diameter	Diameter of propeller blades, tip to tip, in feet.	propeller_diameter= 5.000  propeller_diameter= 6.4  propeller_diameter = 8.8  propeller_diameter= 6.3
propeller_blades	Integer value indicating the number of blades on thepropeller (2, 3 or 4).	propeller_blades= 2  propeller_blades= 3  propeller_blades = 4  propeller_blades = 3
propeller_moi	Propeller moment of inertia, (slug ft2).	propeller_moi= 3.000  propeller_moi= 6.9  propeller_moi = 24  propeller_moi= 5.0
beta_max	Maximum blade pitch angle for constant speed prop(degrees). (Not used if fixed pitch.).	beta_max= 0  beta_max= 45.0  beta_max = 45  beta_max= 24.0
beta_min	Minimum blade pitch angle for constant speed prop(degrees). (Not used if fixed pitch.).	beta_min= 0  beta_min= 15.2  beta_min = 15.2  beta_min = 15.6
min_gov_rpm	The minimum rpm controlled by the governor for aconstant speed prop.	min_gov_rpm= 0  min_gov_rpm= 1100.0  min_gov_rpm = 25520  min_gov_rpm= 800
prop_tc	Time constant for prop.	prop_tc= 0.100  prop_tc= 0.1  prop_tc = 0.004  prop_tc= 0
gear_reduction_ratio	The reduction ratio from the engine output rpm to proprpm.	gear_reduction_ratio= 1.000  gear_reduction_ratio= 1.0  gear_reduction_ratio = 17.6  gear_reduction_ratio = 17.4
fixed_pitch_beta	Blade pitch angle for fixed pitch prop (degrees). (Notused if constant speed.).	fixed_pitch_beta= 28.000  fixed_pitch_beta= 0.0  fixed_pitch_beta = 0  fixed_pitch_beta= 20
low_speed_theory_limit	The speed at which low-speed propeller theory getsblended into the high speed propeller theory, (feet/second).	low_speed_theory_limit=80.000  low_speed_theory_limit= 80.0  low_speed_theory_limit = 80
prop_sync_available	Boolean to indicate if propeller-sync is available(twin engine aircraft); 0 = FALSE, 1 = TRUE.	prop_sync_available= 0  prop_sync_available= 1  prop_sync_available = 1  prop_sync_available = 0
prop_deice_available	Boolean to indicate if propeller de-icing is available;0 = FALSE, 1 = TRUE.	prop_deice_available= 0  prop_deice_available= 1  prop_deice_available = 1
prop_feathering_available	Boolean to indicate if prop feathering is available(constant speed prop only); 0 = FALSE, 1 = TRUE.	prop_feathering_available= 0  prop_feathering_available= 1
prop_auto_feathering_available	Boolean to indicate if prop auto-feathering isavailable (constant speed prop only); 0 = FALSE, 1 = TRUE.	prop_auto_feathering_available=0  prop_auto_feathering_available= 1
min_rpm_for_feather	Minimum rpm at which the prop will feather (iffeathering is available).	min_rpm_for_feather= 700.0  min_rpm_for_feather = 700  min_rpm_for_feather= 0
beta_feather	Propeller pitch angle when feathered (degrees).	beta_feather= 82.5  beta_feather = 79.3  beta_feather= 0
power_absorbed_cf	Coefficient of friction power absorbed by propeller.	power_absorbed_cf=0.9  power_absorbed_cf = 0.9  power_absorbed_cf= 0
defeathering_accumulators_available	Boolean to indicate if de-feathering accumulators areavailable; 0 = FALSE, 1 = TRUE.	defeathering_accumulators_available=0
prop_reverse_available	Specifies the scalar on the calculated propellerreverser effect. A value of 0 will cause no reverse thrust to beavailable. A value of 1.0 will cause the theoretical normal thrust tobe available. Other values will scale the normal calculated valueaccordingly.	prop_reverse_available= 0  prop_reverse_available = 1
minimum_on_ground_beta	Minimum blade pitch angle when the aircraft is on theground (degrees).	minimum_on_ground_beta=0.000  minimum_on_ground_beta= 0.0  minimum_on_ground_beta = 1.0  minimum_on_ground_beta= 0
minimum_reverse_beta	Minimum blade pitch angle when the propeller is inreverse (degrees).	minimum_reverse_beta= 0.000  minimum_reverse_beta= 0.0  minimum_reverse_beta = -14.0  minimum_reverse_beta= 0
thrust_scalar	Parameter that scales the calculated thrust provided bythe propeller.	thrust_scalar=1.000  thrust_scalar = 1.0  thrust_scalar = 1.0
feathering_switches	Boolean indicating if feathering switches areavailable. 0 = FALSE, 1 = TRUE. Feathering switches, allow the pilot to automatically feather the propellervia a switch, regardless of the propeller lever position.	feathering_switches = 1
number_of_propellers	Thenumber of propellers driven per engine.
engine_map	Setof flags that allows the propellers to be driven by a different engine.
propeller.0 to propeller.1	Thisparameter allows for the propeller to be located at the specifiedoffset (longitudinal, lateral and vertical) in feet from the enginethat is driving it.

[magneticcompass]

This section defines the magnetic compass characteristics of the aircraft.

 

Property	Description	Examples
compass.0	Set to 1 for a vertical compass (with no dip errors).	Compass.0 = 1

 

[gpws]

This section sepcifies the details of the ground proximity warning system.

 

Property	Description	Examples
max_warning_height	The height below which a warning is activated.	max_warning_height = 1000
sink_rate_fpm	If an aircraft exceeds this rate of descent a warning is activated.	sink_rate_fpm = -1500
excessive_sink_rate_fpm	If an aircraft exceeds this rate of descent an urgent warning is activated.	excessive_sink_rate_fpm = -2000
climbout_sink_rate_fpm	If an aircraft starts to descend during takeoff, and exceeds this rate of descent, a warning is activated.	climbout_sink_rate_fpm = -100
flap_and_gear_sink_rate_fpm	If an aircraft is landing, and exceeds this rate of descent without flaps or gear extended, a warning is activated.	flap_and_gear_sink_rate_fpm= -100

 

[cameradefinition.n]

This section shows the camera properties most used by aircraft. An aircraft can have multiple cameradefinition sections, which shouldbe numbered from 0 to n. For a full definition of all the properties that can be set for a camera definition, refer to the Camera Configuration document. All of the properties described in that document can be used in an aircraft camera definition in an aircraft configuration file.

Property	Examples
title	Title = "Right Side Window"  Title = "Right Wing"  Title = "Right Float"  Title = "Tail"
guid	Guid ={54F54B8A-3EC2-2D4E-8D10-B8F9D0F16ACC}  Guid ={C690EAFD-223A-42d0-99E0-681ADF93BB59}
description	Description = "View of theright wing from the passenger cabin"  Description = "View from the right wingtip looking at the cockpit"  Description = "View from the aft endof the right float looking forward"  Description = "Looking forward from the tip ofthe vertical stabilizer"
origin	Origin = Center  Origin = Virtual Cockpit
snappbhadjust	SnapPbhAdjust = Swivel  SnapPbhAdjust = None
snappbhreturn	SnapPbhReturn = FALSE
panpbhadjust	PanPbhAdjust = Swivel  PanPbhAdjust = None
panpbhreturn	PanPbhReturn = FALSE
track	Track = None
showaxis	ShowAxis = FALSE  ShowAxis = TRUE
allowzoom	AllowZoom = TRUE  AllowZoom = FALSE
initialzoom	InitialZoom = 1.0  InitialZoom = 0.75  InitialZoom = .5  InitialZoom = 0.4
showweather	ShowWeather = Yes
initialxyz	InitialXyz = 5.5, 0.75, -13  InitialXyz = 7.5, 0.75, 0  InitialXyz = 1.5, .5, -3.9  InitialXyz = 0, 2.0, -3.9
initialpbh	InitialPbh = 0, 0, 95  InitialPbh = 5, 0, 270  InitialPbh = 0, 0, 0  InitialPbh = 10, 0, 0
xyzadjust	XyzAdjust = TRUE
category	Category=Aircraft  Category = VC
momentumeffect	MomentumEffect=TRUE  MomentumEffect = TRUE
clipmode	ClipMode=Minimum
zoompanscalar	ZoomPanScalar = 1.0
showlensflare	ShowLensFlare=FALSE

[turboprop_engine]

The amount of power generated by an engine and the powerrequired for a propeller to turn through the air determine the increaseand decrease of the rpm.  A turboprop engine is really acombination of a turbine engine and a propeller.  The valuesin this section are included to modify valuesspecific to the turboprop.

Property	Description	Examples
power_scalar	Changing this value affects the amount of powerdelivered by the engine to the propellor shaft.	power_scalar = 1.0  power_scalar = 1.0
maximum_torque	Maximum shaft-torque available from the engine(ft-lbs).	maximum_torque = 3270  maximum_torque = 1865  maximum_torque = 7878
powerspecificfuelconsumption	Brake power specific fuel consumption (turboprop only).	PowerSpecificFuelConsumption = 0.55

[airspeed_indicators]

This section is used to define the characteristics of theairspeed indicators on the instrument panels.  The list ofindicators should be listed in order: 0,1,2,…n. These characteristics define the calibration between calibratedairspeed and indicated airspeed. 

Property	Description	Examples
airspeed_indicator.0 to airspeed_indicator.n	The first parameter is ascalar on the calibrated airspeed, and the second is an offset inknots.  The offset is applied first, then thescalar.  The default value for the scalar is 1.0 and thedefault for the offset is 0.0, thus by default indicated airspeed isequal to calibrated airspeed.	airspeed_indicator.0 =1.183, -24.75  airspeed_indicator.0 = 1, 0  airspeed_indicator.0 = 1.3, -24.0

[pressurization]

This section defines the presssurization characteristics of the aircraft.

 

Property	Description	Examples
design_cabin_pressure		design_cabin_pressure =0
max_pressure_differential		max_pressure_differential= 0

[variometers]

This section defines the variometers characteristics of the aircraft.

 

Property	Description	Examples
variometer.0		variometer.0=1

[yaw_string]

This section defines the yaw string characteristics of the aircraft.

 

Property	Description	Examples
yaw_string_available		yaw_string_available=1

[waterballast system]

This section defines the water ballast system of the aircraft.

 

Property	Description	Examples
tank.0	Front Fuselage.	Tank.0 = 7.79, -2.75, 0.0, 0.0, 1
tank.1	Rear Fuselage.	Tank.1 = 3.57, -3.28, 0.0, 0.0, 2
tank.2	Left Outboard.	Tank.2 = 9.25, -0.60, -10.5, 0.0, 2
tank.3	Left Inboard.	Tank.3 = 16.38, -0.66, -4.5, 0.0, 1
tank.4	Right Inboard.	Tank.4 = 16.38, -0.66, 4.5, 0.0, 1
tank.5	Right Outboard.	Tank.5 = 9.25, -0.60, 10.5, 0.0, 2
numberofreleasevalves	Number of release valves.	NumberOfReleaseValves = 2
dumprate	Gallons per second.	DumpRate = 0.18494

[smokesystem]

The section describes how to configure a smoke system for anaircraft. You can set multiple smoke points on anaircraft.

Property	Description	Examples
smoke.0 to smoke.n	The position relative to datum reference point of the smoke emitter and the smoke effect file name.	smoke.0=-10.00, -0.70, 0.0,fx_smoke_w

[folding_wings]

This section describes the folding wing characteristics of the aircraft. Note that these are folding wings used to store an aircraft more compactly when on the ground, or on deck, and not the variable sweep wings used on some supersonic aircraft. Variable sweep wings are not supported.

 

Property	Description	Examples
wing_fold_system_type	One of: 0: None (the default) 1: Manual 2: Pneumatic 3: Electrical 4: Hydraulic	wing_fold_system_type = 1    wing_fold_system_type = 4
fold_rates	Two values (for left and right), giving the percentage per second, to fully extend and retract.	fold_rates = 0.25,0.20    fold_rates = 0.12,0.11

[anemometers]

This section describes the positions of the anemometers in the aircraft.

 

Property	Description	Examples
anemometer.0 to anemometer.n	Position of the anemometer relative to datum reference point.	anemometer.0 = -10.0, 0.0, 2.7  anemometer.0 = 9.6, 0.0, -2.2

[realismconstants]

This section describes some realism constraints, dealing in particular with early aircraft. The values entered are used to make an aircraft more stable.

 

Property	Description	Examples
rollmomentfrombeta	Scalar and offset applied to the roll moment from beta.	RollMomentFromBeta = -0.5, 0
rollmomentfromailerons	Scale and offset applied to the roll moment from the ailerons.	RollMomentFromAilerons = 1.5, 0
pitchmomentzeroalpha	Scale and offset applied to the zero angle of attack.	PitchMomentZeroAlpha = 1.0, 0.002

---

Helicopter Specific Sections (Work in Progress)

The following sections are specific to helicopters only. These sections are a work in progress.

Additional Helicopter Sections

[sling.n]

There can be multiple sling positions on an aircraft, each with its own set of the following properties.

 

Property	Description	Examples
hoist_extend_rate	Feet per second.	hoist_extend_rate = 5
hoist_retract_rate	Feet per second.	hoist_retract_rate = -5
position	Position relative to datum reference point.	position = -34.7, 6.7, 7.0
max_stretch	Max stretch distance at ultimate load.	max_stretch = 2.0
damping_ratio	0 for no damping to 1.0 for critically damped.	damping_ratio = 0.6
rated_load	Characteristics tension of cable in pounds.	rated_load = 600
ultimate_load	Breaking force in pounds. This cannot exceed 10,000lb.	ultimate_load = 2250
tolerance_angle	Angle, in degrees, used to determine lateral breaking force limit.	tolerance_angle=45
auto_pickup_range	Max Range, in feet, for auto-pickup.	auto_pickup_range = 8
auto_pickup_max_speed	Maximum speed (feet per second) for auto-pickup.	auto_pickup_max_speed = 8.5
hoist_payload_station	Payload station in which the hoist will load in and out of. 1 is first station.	hoist_payload_station = 4
hoist_door	Door associated with hoist. Must be open for use.	hoist_door=1

[turboshaft_engine]

A turboshaft engine on a helicopter is very similar to a turboprop engine on a fixed wing aircraft.

 

Property	Description	Examples
power_scalar	Scalar on Turboprop power.	power_scalar = 1.0
maximum_torque	Maximum torque available (ft-lbs).	maximum_torque = 1335
powerspecificfuelconsumption	Brake power specific fuel consumption.	PowerSpecificFuelConsumption = 0.55

 

Standard Helicopter Sections

[helicopter]

Property	Description	Examples
lift_aero_center	The longitudinal position, in feet, from the datum of the helicopter that represents the vertical aerodynamic center.	lift_aero_center = -34.0
reference_length	The length of the helicopter, in feet.	reference_length = 21.58
reference_frontal_area	The cross section area of the fuselage, in feet squared, as viewed from head on to the helicopter.	reference_frontal_area = 17.7
reference_side_area	Total side area of the fuselage, in feet squared, as viewed from directly abeam of the helicopter.	reference_side_area = 44.5
side_aero_center	The longitudinal position, in feet, from the datum of the helicopter that represents the lateral aerodynamic center.	side_aero_center = -12.5
right_trim_scalar	Scalar on the effect of the trim that counters dissymmetry of lift.  The trim normally induces a roll moment to the right, but a negative value will create a left moment.	right_trim_scalar = 1.0
correlator_available	This flag determines if a collective/throttle correlator is configured on the helicopter.	correlator_available = 1
governed_pct_rpm_ref	Defines the percent rpm that the governor attempts to maintain.  1.0 = 100% of “rated” rpm, although a few percent above that is normal.	governed_pct_rpm_ref = 1.04
governor_pid	Proportional – Integral – Derivative (PID) feedback controller that works to maintain the reference rpm.  The series of numbers are: proportional controller constant integral controller constant derivative controller constant max rpm error (where 1.0 = 100%) in which the integrator portion is active max rpm error (where 1.0 = 100%) in which the derivative portion is active	governor_pid = 0.4, 0, 0.1, 0, 0.2
rotor_brake_scalar	Scalar on the effect of the rotor brake.	rotor_brake_scalar = 1.0
torque_scalar	Scalar on the effect that the rotor has on the yawing moment of the helicopter.	torque_scalar = 1.0
cyclic_roll_control_scalar	Scalar on the amount of roll control authority from lateral movement of the cyclic.	cyclic_roll_control_scalar =1.0
cyclic_pitch_control_scalar	Scalar on the amount of pitch control authority from fore/aft movement of the cyclic.	cyclic_pitch_control_scalar =1.0
pedal_control_scalar	Scalar on the amount of yaw control authority from movement of the anti-torque pedals.	pedal_control_scalar =1.0
collective_on_rotor_torque_scalar	Scalar on the amount of torque exerted on the rotor system due to the collective pitch of the rotor blades.  Increasing this constant will result in the rotor rpm tending to decelerate more dramatically as collective is increased.	collective_on_rotor_torque_scalar = 1.0

[fuselage_aerodynamics]

Property	Description	Examples
drag_force_cf	Coefficient of longitudinal drag.	drag_force_cf = 0.55
side_drag_force_cf	Coefficient of lateral drag.	side_drag_force_cf = 10.0
pitch_damp_cf	Pitch damping coefficient (resistance to pitchvelocity).	pitch_damp_cf = -2.0
roll_damp_cf	Roll damping coefficient (resistance to roll velocity).	roll_damp_cf = -2.0
yaw_damp_cf	Yaw damping coefficient (resistance to yaw velocity).	yaw_damp_cf = -0.1
yaw_stability_cf	Yaw stability coefficient. This is the weathervaneeffect.	yaw_stability_cf = 0.27

[mainrotor]

Property	Description	Examples
static_pitch_angle	When the stick is centered, the pitch angle of the rotor disk, in degrees.	static_pitch_angle = 2
static_bank_angle	When the stick is centered, the bank angle of the rotor disk, in degrees.	static_bank_angle = 0
position	Position relative to datum reference point. Thisposition should be the center of the main rotor.	Position = -8.5, 0, 4.91
radius	The radius of the rotor, in feet.	Radius = 12.583
max_disc_angle	The maximum absolute deflection angle up or down, indegrees, that the rotor disc can move with the cyclic.	max_disc_angle = 5.0
ratedrpm	The rated rpm value for the main rotor.	RatedRpm = 510
number_of_blades	The number of blades in the rotor.	Number_of_blades = 2
weight_per_blade	Approximate weight, in pounds, of each rotor blade.	Weight_per_blade = 26.0
weight_to_moi_factor	The constant used in calculating the moment of inertiaof the rotor disc. The MOI algorithm is a function of the number ofblades, their weight, and this constant. Increasing this constant willincrease the inertia of the disc.	Weight_to_moi_factor = 0.58
inflow_vel_reference	The reference inflow velocity of the air mass movingthrough the rotor disc. Increasing this value will result in morethrust being generated.	inflow_vel_reference = 34.0

[secondaryrotor]

Property	Description	Examples
position	Position relative to datum reference point. Thisposition should be the center of the secondary rotor.	Position = -67.6, -3.7, 11.6  Position = -22.8, -0.74, 1.8
tailrotor	This flag, if set to 1, configures the secondary rotoras a tail rotor, or anti-torque.	TailRotor = 1
radius	The radius of the rotor, in feet.	Radius = 6.56  Radius = 1.75

 

---

Model, Sound, Texture and Panel Files

The panel.cfg File

The panel.cfg file is located in an aircraft’s Panel folder,and defines the characteristics of the aircraft’s cockpit,including window settings, view settings, and gauges.

The model.cfg File

The model.cfg file is located in an aircraft’s Model folder,and specifies which visual models (.mdl files), exterior and interior, to render during normalflight and optionally after a crash. When designing new models, it is required that the model file be separated into the two parts.

[models]

 

Property	Description	Examples
normal	External 3D model used under normal circumstances.	normal=Diamond_DA42
interior	Internal, virtual cockpit, model.	interior=Diamond_DA42_interior

 

The sound.cfg File

The sound.cfg file is located in an aircraft’s Sound folder,and defines the sounds to use for that aircraft (such as the sound ofthe engine at various speeds, the sound of the landing gear going down,and so on). Refer to the Sound Configuration files document for moredetails.

The Texture Folder

An aircraft’s textures are defined by the .bmp files in the aircraft’s Texture folder, and are projected onto the aircraft’s parts as specified in the aircraft’s visual model (.mdl) file, located in the Model folder. Texture file names must correspond to the texture files that are referenced in the .mdl file. If the file names don't correspond, the textures will not be rendered.
Texture files are mipmapped.  A mipmapped texture consists of a sequence of images, each of which is a progressively lower resolution, prefiltered representation of the same image. Mipmapping is a computationally low-cost way of improving the quality of rendered textures. Each prefiltered image, or level, in the mipmap is a power of two smaller than the previous level. A high-resolution level is used for objects that are close to the viewer. Lower-resolution levels are used as the object moves farther away.
To edit a mipmapped texture, you’ll need to use Image Tool, an image editing application included with the SDK. Be sure to save a copy of the original file before attempting to modify it. A texture can also be edited using a simple graphics application such as Paint, though it will be saved as a standard .bmp file instead of a mipmapped .bmp. Flight Sim World will automatically generate the mipmaps for the texture, although these mipmaps may notbe of as high a quality as mipmaps created using ImageTool.

Notes on using Aliasing

Aliasing allows multiple aircraft, or other objects such as vehicles or boats, to use the samefiles(panels, flight models, sounds, etc.). This saves disk space and makesfile organization more efficient. You can alias an object ’spanel.cfg, model.cfg, and sound.cfg files from any otherobject. Whereas configuration sets allow objects withina single container to share components, aliasing allowsobjects in different containers to share components. To alias a panel.cfg, model.cfg, or sound.cfgfile, simply change the aliasing object's configuration file to read:

 

[fltsim]
alias=objectname\panel
or
[fltsim]
alias=objectname\model
or
[fltsim]
alias=objectname\sound

Aliased files are searched for in the following order:

1. Relative path from the object type folder (one of: Airplanes, Animals, Boats, GroundVehicles, Misc or Rotorcraft).
2. Relative path from the Flight Sim World  folder.

An example

Let’s say you’ve imported a Diamond DA42 aircraftvariant into the simulation, but want to use the G1000 panel from the existing Diamond DA42 when flying it. Instead of duplicating all the existing DA42 panel files(Panel.cfg and .bmps) and putting them in the new DA42 aircraftcontainer, you can alias to them in their existing location from theDA42 panel.cfg file. Just change the new DA42 panel.cfg file to read:

[fltsim]
alias=DA42\panel

The new DA42 aircraft would then use the DA42 panel.cfg file (and the associated .bmps). The syntax for aliasing model.cfg and sound.cfg files is identical.