The aircraft configuration file (aircraft.cfg) represents the highest level of organization within an aircraft container. Each aircraft has its own configuration file located in its container (aircraft folder). For example, the Mooney Bravo aircraft.cfg can be found at:
SimObjects\Airplanes\Mooney_Bravo\aircraft.cfg
The aircraft.cfg file specifies the versions of the aircraft included in the aircraft container, as well as the attributes (name, color, sound, panels, gauges, and so on) for each aircraft and where to find the files that define those attributes. Within the aircraft.cfg file there are a number of sections. Brackets enclosing the section name identify the various sections. In order for the simulation to make proper use of any variable, it is important that the variable be located in the correct section. While exact spelling is important, none of the terms is case-sensitive.
The SimObjects.cfg file contains entries to determine which paths to search for aircraft and other containers. For example:
... |
[Entry.12] |
Path=SimObjects\Airplanes |
... |
Additional paths can be added to this file. The paths are either relative to the root folder of the Prepar3D installation folder, or they are absolute paths -- which can also point to locations on other computers (using the "\\computer name" notation).
The SimObjects.cfg file is in the %PROGRAMDATA%\Lockheed Martin\Prepar3D v4 folder by default. Please see the Add-ons Overview article for more information.
Testing Changes to aircraft.cfg
To see the effects of a change, the aircraft must be reloaded (this is because aircraft are loaded into the memory cache from disk, so you have to flush the cache to enable your changes to take effect). This involves a couple of steps:
- Configure a key command to Reload User Object (which will reload your object from within the simulation). To do this go to Settings, Controls Assignments, and scroll down to the Reload User Object event. By default, it's unassigned. Use Change Assignment to configure a keystroke combination for this event. Once assigned, you can use this key command to reload the aircraft within the simulation.
- Turn off AI Traffic. AI traffic aircraft are maintained in the cache and even if you update the aircraft you are currently piloting, if the same aircraft is being used by AI traffic, then your cache won't get updated automatically by simply reloading the plane. So to ensure your aircraft is reloaded from disk, you must also go to the Settings Screen, choose Traffic, and set the Air Traffic Density slider all the way to the left to 0%.
- Now you can test changes made to an aircraft.cfg within the simulation by using
the Reload User Object key command after each change, or set of changes, is made.
Any errors made in creating or editing the aircraft.cfg file will show up, along with the following error messages, while an aircraft is being loaded. The error messages are listed in order; that is, the first error message represents an error early in the aircraft-loading process.
Error Message | Description |
---|---|
Aircraft initialization failure. | Indicates that some essential files are missing from the aircraft container. If the files are missing, the aircraft will not usually be displayed in the Select Vehicle dialog box; as a result, this error is rare. |
Failed to start up the flight model. | The .air file was not loaded successfully. |
This is not a Prepar3D aircraft model. | The visual model (.mdl) file for this aircraft is not compatible with Prepar3D. |
Visual model could not be displayed. | An error 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. |
Sections of the Configuration File
[fltsim.n]
Each [fltsim.n] section of an aircraft configuration file represents a different version (configuration) of the aircraft, and is known as a configuration set. Configuration sets allow a single aircraft container to represent several aircraft, and allow those aircraft to share components.
If there is only one section (labeled [fltsim.0]), it is because 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 so on), each one refers to a different version of the aircraft.
For instance, there are several versions of the Mooney Bravo, all housed in the same Mooney Bravo aircraft container (folder). The various versions must vary by their title, and may also vary other items such as the panel, description, and sounds.
While these configuration sets share many components, they can each use different panels. The panel= line in the respective fltsim sections thus refer to the respective panel folder for each aircraft: For example, panel=ifr means that this version of the C172 uses the panel files in the panel.ifr subfolder.
When creating and referencing multiple model, panel, sound, and texture directories, use the naming convention foldername for all common files between all vehicle versions and foldername.extension for files unique to each vehicle version, where the extension is a unique identifier for that configuration set (for example, .ifr). To refer to the folder from the relevant parameter in the aircraft.cfg file, just specify the extension (for example, panel=ifr).
The parameters in each configuration set can refer to the same files, to different files, or to a mix of files. While using different panels, all Cessna configurations use the same sounds, and thus the sound parameters in all the fltsim sections point to the single sound folder in the C172 folder.
Each aircraft defined by a configuration set will appear as a separate listing in the Select Vehicle dialog box. The fact that multiple aircraft share some components is hidden from the user. From a user's perspective, they are distinct aircraft (just as if all the common files were duplicated and included in three distinct aircraft containers). From a developer's perspective, the aircraft are really just different configuration sets of the same aircraft. Because they share some files, they make much more efficient use of disk space.
Within each [fltsim.n] section are parameters that define the details of that particular configuration set:
Property | Description | Examples |
---|---|---|
title | The title of the aircraft. The version variation that is being loaded |
Mooney Bravo( title=Mooney Bravo ) |
sim | Specifies which AIR (flight model) file to use. The file is located in the same folder as the aircraft configuration file. Refer to Flight Models for details on how to create an AIR file. |
Mooney Bravo( sim=Mooney_Bravo ) |
model | Specifies which model folder to reference. If no entry is made, the default folder is used. |
Mooney Bravo( model= )
Mooney Bravo with G1000( model=g1000 ) |
panel | Specifies which panel folder to reference. |
Mooney Bravo( panel= ) Mooney Bravo with G1000( panel=g1000 ) |
sound | Specifies which sound folder to reference. | Mooney Bravo( sound= ) |
texture | Specifies which texture folder to reference. |
Mooney Bravo( texture= ) Mooney Bravo Retro( texture=1 ) |
script | Specifies which script folder to reference. |
F-16C( script= ) |
kb_checklists | Specifies which _check.txt file (located in the aircraft folder) to use on the Checklists tab of the kneeboard. | Mooney Bravo( kb_checklists=Mooney_Bravo_Check ) |
kb_reference | Specifies which _ref.txt file (located in the aircraft folder) to use on the Reference tab of the kneeboard. | Mooney Bravo( kb_reference=Mooney_Bravo_ref ) |
atc_id | The tail number displayed on the exterior of the aircraft. This parameter can also be edited from the Select Vehicle dialog (if the atc_id_enable parameter is set to 1). Note that custom tail numbers burned into textures will not be modified by this. | Mooney Bravo( atc_id=N123MS ) |
atc_airline | The ATC system will use the specified airline name with this aircraft. This is dependent on ATC recognizing the name. ATC will treat this aircraft as an airliner when this is used in conjunction with atc_flight_number. | Commercial Airliner( atc_airline=World Travel ) |
atc_flight_number | The ATC system will use this number as part of the aircrafts callsign. ATC will treat this aircraft as an airliner when this is used in conjunction with atc_airline. | |
ui_manufacturer | This value identifies the manufacturer sub-category used to group aircraft in the Select Vehicle dialog in Prepar3D. |
Mooney Bravo( ui_manufacturer="Mooney" ) |
ui_type | This value identifies the type sub-category used to group aircraft in the Select Vehicle dialog in Prepar3D. |
Mooney Bravo( ui_type="Bravo" ) |
ui_variation | This value identifies the variation sub-category used to group aircraft in the Select Vehicle dialog in Prepar3D. | Mooney Bravo Retro( ui_variation="White, Blue" ) |
ui_typerole | This value identifies the role of the aircraft. |
Mooney Bravo( ui_typerole="Single Engine Prop" ) |
ui_createdby | This value is used to identify the creator of the configuration file. | Mooney Bravo( ui_createdby="Lockheed Martin Corporation" ) |
description | The aircraft description can be modified to say whatever you like about the aircraft. This information will be displayed in a description box when the aircraft is selected. (The \s is used to produce a semicolon ( ; ) punctuation mark within the description.). | |
visual_damage | Setting this flag to 1 enables visual damage (e.g. parts breaking off) to be seen when crashing the aircraft into the scenery. Note: visual damage will only work if it is built into the aircrafts .mdl file. | Mooney Bravo( visual_damage=0 ) |
atc_heavy | Setting this flag to 1 will result in the ATC system appending the phrase heavy to the aircrafts callsign. | Mooney Bravo( atc_heavy=0 ) |
atc_parking_types | Specifies the preferred parking for this aircraft, used by ATC. If this line is omitted, ATC will determine parking according to the type of aircraft and parking available. If multiple values are listed, 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. |
de Havilland Dash 8-100( atc_parking_types=RAMP ) CRJ 700( 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, "AAL" for American 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 multiple parking codes are entered, separate them with commas. |
atc_id_color | Specifies, in RGB hexadecimal, the color of the tail number. The first two characters following the 0x specify the red value in hex, the second two characters the green, and the third set the blue. The final two characters are unused. Each value can be between 0 to ff hex, which is 0 to 255 decimal. Note that custom tail numbers burned into textures will not be modified by this. |
King Air 350( atc_id_color=0xffffffff ) |
prop_anim_ratio | The ratio of rotor revolutions rendered to the actual revolutions in the simulator. | Robinson R22( prop_anim_ratio=-1.76 ) |
atc_model | This is the specific aircraft model that the ATC system recognizes for this type of aircraft. | Robinson R22( atc_model=R22 ) |
dis_entity_type | The DIS entity type string specific to this object. The following is an example entity type string (without quotes): "1.2.225.1.6.1.0". Each integer of the string represents properties of the entity type in the following order: Kind, Domain, Country, Category, Subcategory, Specific, and Extra. |
( dis_entity_type=1.2.225.1.6.1.0 ) |
ExternalSecondarySimID.0 to ExternalSecondarySimID.n |
The GUID of External Secondary Sim modules that this SimObject works with. | ( ExternalSecondarySimID.0={3E6B47E7-C706-4A10-BC88-6E7C199ED5A6} ) |
ExternalSecondarySimData.0 to ExternalSecondarySimData.n |
Optional string data you want to pass to this External Secondary Sim module. | ( ExternalSimData=75,75,100 ) |
ExternalSecondarySimVarCount.0 to ExternalSecondarySimVarCount.n |
Optional integer defining the number of custom SimVars to set aside for this External Secondary Sim to use. These SimVars are accessed via the SimVar name "External Secondary Sim Vars Value:index", where index can run from zero to one less than the value set in this item. | ( ExternalSecondarySimVarCount=35 ) |
ExternalSecondarySimModule.0 to ExternalSecondarySimModule.n |
Optional SimConnect module to load when loading this SimObject. | ( ExternalSecondarySimModule=Modules\TestExternalSim.dll ) |
IsSelectableVehicle |
This flag can be used to override whether or not a SimObject can be selected by the user via the Select Vehicle user interface. This flag will also be used to override whether or not the user's avatar can attach to the vehicle. This flag takes precedence over the IsSelectableVehicle value in the [General] section. |
|
static_pitch | The static pitch of the aircraft when at rest on the ground (degrees). The program uses this value to position the aircraft at startup, in slew, and at any other time when the simulation is not actively running. This value takes precedence over the static_pitch value in the [contact_points] section. | |
static_cg_height | The static height of the aircraft when at rest on the ground (feet). The program uses this value to position the aircraft at startup, in slew, and at any other time when the simulation is not actively running. This value takes precedence over the static_cg_height value in the [contact_points] section. | Orion MPCV with SLS Block 1( static_cg_height = 263.0 ) |
visual_model_guid | GUID of a Scenery or Mobile Scenery model to use for the Simulation Object. | ( visual_model_guid = {aae3d3f0-7b62-4aed-8ca1-0c06cc00fd47} ) |
[general]
In addition to the fltsim sections, the general section contains information related to all variations of the aircraft.
Property | Description | Examples |
---|---|---|
atc_type | This is the specific aircraft type that the ATC system recognizes for this type of aircraft. | Mooney Bravo( atc_type=Mooney ) |
atc_model | This is the specific aircraft model that the ATC system recognizes for this type of aircraft. | Mooney Bravo( atc_model=M20T ) |
editable | Unused. | |
performance | The performance description for the aircraft can be edited. The \t is a tab character, and the \n is a new-line character. As the flight model for all variations is the same, the performance of each variation should also be identical. | Mooney Bravo( performance="Maximum Speed\t\n220 kts 253 mph\t407 kmh\n\nCruise Speed\t\n195 kts 224 mph \t361 kmh\n\nEngine\t\nTextron Lycoming TIO-540-AF1B 270 hp\n\nPropeller\t\nThree-bladed McCauley constant speed\n\nMaximum Range\t\n1,050 nm 1,204 sm \t1,945 km\n\nService Ceiling\t\n25,000 ft 7,620 m\n\nFuel Capacity\t\n89 U.S. gal 337 L \n\nEmpty Weight\t\n2,189 lb \t 993 kg\n\nMaximum Gross Weight\t\n3,368 lb \t 1,528 kg\n\nUseful Load\t\n1,179 lb \t 535 kg\n\nLength\t\n26.75 ft\t 8.15 m\n\nWingspan\t\n36 ft\t 11 m\n\nHeight\t\n8.33 ft\t 2.5 m\n\nSeating\t\nUp to 4" ) |
category | For aircraft, one of airplane or helicopter. |
Maule M7 260C( category = Airplane ) Robinson R22( category = Helicopter ) |
IsSelectableVehicle |
This flag can be used to override whether or not a SimObject can be selected by the user via the Select Vehicle user interface. This flag will also be used to override whether or not the user's avatar can attach to the vehicle. By default, vehicles are considered user selectable if the following conditions are true:
|
Tracker Sample( IsSelectableVehicle=True ) |
RecordAndPlaybackDefinitionGuid | Used to specify a custom RecordAndPlayback.xml file. | See the Simulation Recording and Playback article. |
DISArticulatedPartDefinitionGuid | Used to specify a custom DISArticulatedParts.xml file. | See the Custom Articulated Parts XML File section of the DIS article. |
CigiArticulatedPartDefinitionGuid | Used to specify a custom CigiArticulatedParts.xml file. | See the Custom Articulated Parts XML File section if the CIGI article. |
[pitot_static]
The vertical_speed_time_constant parameter can be used to tune the lag of the Vertical Speed Indicator for the aircraft:
- Increasing the time constant decreases the lag, making the gauge react more quickly.
- Decreasing the time constant increases the lag, making the gauge react more slowly.
- A value of 0 effectively causes the indication to freeze. If an instantaneous indication is desired, use an excessively large value, 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 speed indicator. Increasing will cause a more instantaneous reaction in the VSI. | Mooney Bravo( vertical_speed_time_constant = 1.0 ) |
pitot_heat | Scale of heat effectiveness, or 0 if not available. | Mooney Bravo( pitot_heat = 1.0 ) |
[weight_and_balance]
The weight and center of gravity of the aircraft can be affected through the following parameters.
Note
- In the stock aircraft, the station_load.0, 1, etc. parameters are enclosed in quotation marks. These are used by internal language translation tools.
Moments of Inertia
A moment of inertia (MOI) defines the mass distribution about an axis of an aircraft. A moment of inertia for a particular axis is increased as mass is increased and/or as the given mass is distributed farther from the axis. This is largely what determines the inertial characteristics of the aircraft.
The following weight and balance parameters define the MOIs of the empty 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 on aircraft material, installed equipment, and number of engines and their positions.
Property | Description | Examples |
---|---|---|
max_gross_weight | Maximum design gross weight of the aircraft. | Mooney Bravo( max_gross_weight = 3368 ) |
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. | Mooney Bravo( empty_weight = 2189 ) |
reference_datum_position | Offset (in feet) of the aircraft's reference datum from the standard center point, which is on the centerline chord aft of the leading edge. By adjusting this position, actual aircraft loading data can be used directly according to the aircraft's manufacturer. If not specified, the default is 0,0,0. | Mooney Bravo( reference_datum_position = 3.9, 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 . | Mooney Bravo( empty_weight_CG_position = -3.7, 0, 0 ) |
max_number_of_stations | Specifies the maximum number of stations (specific locations) for the aircraft when it is loaded. This does allow an unlimited number of stations to be specified, but 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. |
Mooney Bravo( 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. The first parameter number on each line specifies the weight (in pounds), followed by the offset relative to 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. |
Mooney Bravo( station_load.0 = 170, -3.1, -1.5, 0.0 ) |
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 the station name can also follow the station_load information. |
Mooney Bravo( station_name.1 = "Front Passenger" ) |
empty_weight_pitch_moi | The moment of inertia (MOI) about the lateral axis. | Mooney Bravo( empty_weight_pitch_MOI = 2706 ) |
empty_weight_roll_moi | The moment of inertia (MOI) about the longitudinal axis. | Mooney Bravo( empty_weight_roll_MOI = 2131 ) |
empty_weight_yaw_moi | The moment of inertia (MOI) about the vertical axis. | Mooney Bravo( empty_weight_yaw_MOI = 3932 ) |
empty_weight_coupled_moi | The moment of inertia (MOI) about the roll and yaw axis (usually zero). |
Mooney Bravo( empty_weight_coupled_MOI= 0.0 ) Bombardier CRJ 700( empty_weight_coupled_MOI = 0.0 ) |
[flight_tuning]
Flight control effectiveness parameters
The elevator, aileron and elevator effectiveness parameters are multipliers on the default power of the control surfaces. For example, a value of 1.1 increases the effectiveness by 10 percent. Likewise, a value of 0.9 decreases the effectiveness by 10 percent. A negative number reverses the normal effect of the control. Omission of a parameter results in the default value of 1.0.
Stability parameters
The pitch, roll and yaw parameters are multipliers on the default stability (damping effect) about the corresponding axis of the airplane. For example, a value of 1.1 increases the damping by 10%. Likewise, a value of 0.9 decreases the damping by 10%. A negative number results in an unstable characteristic about the axis. A positive damping effect is simply a moment in the direction opposite of the rotational velocity. Omission of a parameter will result in the default value of 1.0.
Lift parameter
The cruise_lift_scalar parameter is a multiplier on the coefficient of lift at zero angle of attack Cruise lift in this context refers to the lift at relatively small angles of attack, which is typical for an airplane in a cruise condition. This scaling is decreased linearly as angle of attack moves toward the critical (stall) angle of attack, which prevents destabilizing low speed and stall characteristics at high angles of attack. Modify this value to set the angle of attack (and thus pitch) for a cruise condition. A negative value is not advised, as this will result in extremely unnatural flight characteristics. Omission of this parameter results in the default value of 1.0.
High Angle of Attack parameters
The hi_alpha_on_roll and hi_alpha_on_yaw parameters are multipliers on the effects on roll and yaw at high angles of attack. The default values are 1.0.
Propeller-induced turning effect parameters
The p_factor_on_yaw, torque_on_roll, gyro_precession_on_pitch and gyro_precession_on_yaw parameters are multipliers on the effects induced by rotating propellers. These are often called "left turning 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 aircraft speed and acceleration. There are two basic types of drag that the user can adjust here. Parasitic drag is composed of two basic elements: form drag, which results from the interference of streamlined airflow, and skin friction. Parasite drag increases as airspeed increases. Induced drag results from the production of lift. Induced drag increases as angle of attack increases.
The parasite_drag_scalar and induced_drag_scalar parameters are multipliers on the two respective drag coefficients. For example, a value of 1.1 increases the respective drag component by 10 percent. A value of 0.9 decreases the drag by 10 Percent. Negative values are not advised, as extremely unnatural flight characteristics will result. The default values are 1.0.
Property | Description | Examples |
---|---|---|
cruise_lift_scalar | CL0. | Mooney Bravo( cruise_lift_scalar = 1.0 ) |
parasite_drag_scalar | Cd0. |
Mooney Bravo( parasite_drag_scalar = 1.0 ) |
induced_drag_scalar | Cdi. |
Mooney Bravo( induced_drag_scalar = 1.0 ) |
elevator_effectiveness | Cmde. |
Mooney Bravo( elevator_effectiveness = 1.0 ) |
aileron_effectiveness | Clda. |
Mooney Bravo( aileron_effectiveness = 1.0 ) |
rudder_effectiveness | Cndr. |
Mooney Bravo( rudder_effectiveness = 1.0 ) |
pitch_stability | Cmq. |
Mooney Bravo( pitch_stability = 1.0 ) |
roll_stability | Clp. |
Mooney Bravo( roll_stability = 1.0 ) |
yaw_stability | Cnr. |
Mooney Bravo( yaw_stability = 1.0 ) |
elevator_trim_effectiveness | Cmdetr. |
Mooney Bravo( elevator_trim_effectiveness = 1.0 ) |
aileron_trim_effectiveness | Cldatr. |
Mooney Bravo( aileron_trim_effectiveness = 1.0 ) |
rudder_trim_effectiveness | Cndrtr. |
Mooney Bravo( rudder_trim_effectiveness = 1.0 ) |
hi_alpha_on_roll | See notes above. | |
hi_alpha_on_yaw | ||
p_factor_on_yaw | See notes above. | Piper Cub( p_factor_on_yaw = 0.3 ) |
torque_on_roll | Piper Cub( torque_on_roll = 0.3 ) | |
gyro_precession_on_yaw | See notes above. | Piper Cub( gyro_precession_on_yaw = 0.3 ) |
gyro_precession_on_pitch | Piper Cub( gyro_precession_on_pitch = 0.3 ) |
[generalenginedata]
Every type of aircraft, even a glider, should have this section in the aircraft.cfg file. Basically, this section describes the type of engine, the number of engines, where the engines are located, and a fuel flow scalar to modify how much fuel the engine requires to produce the calculated power.
Property | Description | Examples |
---|---|---|
engine_type | Integer that identifies what type of engine is on the aircraft. 0 = piston, 1 = Jet, 2 = None, 3 = Helo-turbine, 4 = Rocket (not supported) 5 = Turboprop. | Mooney Bravo( engine_type = 0 ) |
engine.0 to engine.n |
Offset of the engine from the datum reference point. Each engine location specified increases the engine count (maximum of four engines allowed). |
Mooney Bravo( Engine.0 = 2.1, 0.0, 0.0 ) |
fuel_flow_scalar | Scalar for modifying the fuel flow required by the engine(s). A value of less than 1.0 causes a slower fuel consumption for a given power setting, a value greater than 1.0 causes the aircraft to burn more fuel for a given power setting. | Mooney Bravo( fuel_flow_scalar = 1.0 ) |
min_throttle_limit | Defines the minimum throttle position (percent of max). Normally 0 for piston aircraft and -0.25 for turbine airplane engines with reverse thrust. | Mooney Bravo( min_throttle_limit = 0.0 ) |
max_contrail_temperature | Ambient temperature, in Celsius, in which engine vapor contrails will turn on. The default value is about -39 degrees Celsius for turbine engines. For piston engines, the contrail effect is turned off unless a temperature value is set here. | Commercial Airliner( 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. | |
starter_type | Set to 1 for a Manual Starter | |
thrustanglepitchheading.0 | Thrust pitch and heading angles in degrees ( positive pitch down, positive heading right). | |
default_oil_leak_rate | The default maximum rate that oil will leak when the malfunction is selected. This rate is specified as percent per second. | default_oil_leak_rate = 0.05 (20 seconds for total leak) |
pct_oil_pressure_on_failure | The percentage of max oil pressure in which the pressure will drop with a 100% failure of the oil system. Default is 0. This may be useful if it is desired that the pressure does not drop to zero under failure. | pct_oil_pressure_on_failure = 0.55 |
[turbineenginedata]
A turbine engine ignites fuel and compressed air to create thrust. These parameters define the power (thrust) output of a given jet turbine engine.
Property | Description | Examples |
---|---|---|
fuel_flow_gain | Fuel flow gain constant. | Bombardier CRJ 700( fuel_flow_gain = 0.0025 ) |
fuel_flow_gain.n | Fuel flow gain constant table. This can be used in lieu of the single constant (above) in order to make the fuel flow gain a function of N1. The table will load sequentially (.0, .1, .2, ...) up to a maximum of 5 entries. Each entries first value is the N1 input, the second is the scalar at that N1. The constant will be linearly interpolated in between data points. |
fuel_flow_gain.0 = 00.0, 0.011 fuel_flow_gain.1 = 25.0, 0.011 fuel_flow_gain.2 = 60.0, 0.05 |
inlet_area | Engine nacelle inlet area, (in square feet). | Bombardier CRJ 700( inlet_area = 9.4 ) |
rated_n2_rpm | Second stage compressor rated rpm. | Bombardier CRJ 700( rated_N2_rpm = 29920 ) |
static_thrust | Maximum rated static thrust at sea level (lbs). | Bombardier CRJ 700( static_thrust = 12670 ) |
afterburner_available | A number, indicating the number of afterburner stages available. | Bombardier CRJ 700( afterburner_available = 0 ) |
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. |
Bombardier CRJ 700( reverser_available = 1 ) |
thrustspecificfuelconsumption | Jet thrust specific fuel consumption. The ratio of fuel used in pounds per hour, to thrust in pounds. Applies at all speeds. | |
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. | |
afterburner_throttle_threshold | Percentage of throttle range when the afterburner engages. |
[jet_engine]
The thrust_scalar parameter scales the calculated thrust for jet engines (thrust taken from the [TurbineEngineData] section).
Property | Description | Examples |
---|---|---|
thrust_scalar | Parameter that scales the calculated thrust provided by the propeller. | Bombardier CRJ 700( thrust_scalar = 1.0 ) |
[electrical]
These parameters configure the characteristics of the aircraft's electrical system and its components. Each aircraft has a battery as well as an alternator or generator for each engine.
Below is a table of electrical section parameters shown with default values for Bus Type, Max Amp Load and Min Voltage (the values applied if the parameters are omitted). The default Min Voltage equals 0.7*Max Battery Voltage. The list of components also reflects all of the systems currently linked to the electrical system. If a component is included in the list but the aircraft does not actually have that system, the component is simply ignored.
Bus Type
Specifies which bus in the electrical system the component is connected to, according to the following bus type codes:
Bus Type | Bus |
---|---|
0 | Main Bus (most components connected here) |
1 | Avionics Bus |
2 | Battery Bus |
3 | Hot Battery Bus (bypasses Master switch) |
4 | Generator/Alternator Bus 1 (function of engine 1) |
5 | Generator/Alternator Bus 2 (function of engine 2) |
6 | Generator/Alternator Bus 3 (function of engine 3) |
7 | Generator/Alternator Bus 4 (function of engine 4) |
Max Amp Load
Max Amp Load is the current required to power the component, and of course becomes the additional load on the electrical system.
Min Voltage
Min Voltage is the minimum voltage required from the specified bus for the component to function.
Property | Description | Examples |
---|---|---|
flap_motor | Bus type, max amp, min voltage | Mooney Bravo( flap_motor = 0, 5 , 17.0 ) |
gear_motor | Bus type, max amp, min voltage | Mooney Bravo( gear_motor = 0, 5 , 17.0 ) |
autopilot | Bus type, max amp, min voltage | Mooney Bravo( autopilot = 0, 5 , 17.0 ) |
avionics_bus | Bus type, max amp, min voltage |
Mooney Bravo( avionics_bus = 0, 5, 17.0 ) Bombardier CRJ 700( avionics_bus = 0, 5 , 9.5 ) |
avionics | Bus type, max amp, min voltage |
Mooney Bravo( avionics = 1, 5 , 17.0 ) Bombardier CRJ 700( avionics = 1, 5 , 9.5 ) |
pitot_heat | Bus type, max amp, min voltage | Mooney Bravo( pitot_heat = 0, 2 , 17.0 ) |
additional_system | Bus type, max amp, min voltage |
Mooney Bravo( additional_system = 0, 2, 17.0 ) Bombardier CRJ 700( additional_system = 0, 2 , 9.5 ) |
marker_beacon | Bus type, max amp, min voltage |
Mooney Bravo( marker_beacon = 1, 2 , 17.0 ) Bombardier CRJ 700( marker_beacon = 1, 2 , 9.0 ) |
gear_warning | Bus type, max amp, min voltage | Mooney Bravo( gear_warning = 0, 2 , 17.0 ) |
fuel_pump | Bus type, max amp, min voltage |
Mooney Bravo( fuel_pump = 0, 5 , 17.0 ) Bombardier CRJ 700( fuel_pump = 0, 5 , 9.0 ) |
starter1 | Bus type, max amp, min voltage | Mooney Bravo( starter1 = 0, 20, 17.0 ) |
starter2 | Bus type, max amp, min voltage | |
starter3 | Bus type, max amp, min voltage | |
starter4 | Bus type, max amp, min voltage | |
light_nav | Bus type, max amp, min voltage | Mooney Bravo( light_nav = 0, 5 , 17.0 ) |
light_beacon | Bus type, max amp, min voltage | Mooney Bravo( light_beacon = 0, 5 , 17.0 ) |
light_landing | Bus type, max amp, min voltage | Mooney Bravo( light_landing = 0, 5 , 17.0 ) |
light_taxi | Bus type, max amp, min voltage | Mooney Bravo( light_taxi = 0, 5 , 17.0 ) |
light_strobe | Bus type, max amp, min voltage | Mooney Bravo( light_strobe = 0, 5 , 17.0 ) |
light_panel | Bus type, max amp, min voltage | Mooney Bravo( light_panel = 0, 5 , 17.0 ) |
light_cabin | Bus type, max amp, min voltage | |
prop_sync | Bus type, max amp, min voltage | |
auto_feather | Bus type, max amp, min voltage | |
auto_brakes | Bus type, max amp, min voltage | |
standby_vacuum | Bus type, max amp, min voltage | |
hydraulic_pump | Bus type, max amp, min voltage | |
fuel_transfer_pump | Bus type, max amp, min voltage | |
propeller_deice | Bus type, max amp, min voltage | |
light_recognition | Bus type, max amp, min voltage | |
light_wing | Bus type, max amp, min voltage | |
light_logo | Bus type, max amp, min voltage | |
directional_gyro | Bus type, max amp, min voltage | |
directional_gyro_slaving | Bus type, max amp, min voltage | |
max_battery_voltage | The maximum voltage to which the battery can be charged. It is also the voltage available from the battery when the aircraft is initialized. The battery voltage will decrease from this if the generators or alternators are not supplying enough current to meet the demand of the active components. |
Bombardier CRJ 700( max_battery_voltage = 24.0 ) DeHavilland Beaver DHC2( max_battery_voltage = 24 ) |
generator_alternator_voltage | Voltage of the generators or alternators. |
Bombardier CRJ 700( generator_alternator_voltage = 25.0 ) DeHavilland Beaver DHC2( generator_alternator_voltage = 28 ) |
max_generator_alternator_amps | Maximum generator/alternator amps. |
Bombardier CRJ 700( max_generator_alternator_amps = 40.0 ) DeHavilland Beaver DHC2( max_generator_alternator_amps = 50 ) |
engine_generator_map | Array of generator counts, corresponding to the number of engines, indicating how many generators are configured with the engine. | engine_generator_map=1,1 (one generator on engine 1 and one on engine 2) |
electric_always_available | Set to 1 if electric power is available regardless of the state of the battery or circuit. |
[contact_points]
You can configure and adjust the way aircraft reacts to different kinds of contact, including landing gear contact and articulation, braking, steering, and damage accrued through excessive speed. You can also configure each contact point independently for each aircraft, and there is no limit to the number of points you can add. When importing an aircraft that does not contain this set of data, the program will generate the data from the .air file the first time the aircraft is loaded, and then write it to the aircraft.cfg.
Each contact point contains a series of values that define the characteristics of the point, separated by commas. A contact point has 16 parameters, described in the following table:
Contact Point Parameter (and example) | 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 cause damage (feet/min). |
6 (0) | Brake Map |
Defines which brake input drives the brake (wheels only). 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 wheel can pivot (degrees). |
9 (0.25) | Static Compression | This is the distance a landing gear is compressed when the empty aircraft is at rest on the ground (feet). This term defines the "strength" of the strut, where a smaller number will increase the "stiffness" of the strut. |
10 (2.5) | Ratio of Maximum Compression to Static Compression | Ratio of the max dynamic compression available in the strut to 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 reaction oscillations are damped. A value of 1.0 is considered critically damped, meaning there will be little or no oscillation. A damping ratio of 0.0 is considered undamped, meaning that the oscillations will continue with a constant magnitude. Negative values result in an unstable ground handling situation, and values greater than 1.0 might also cause instabilities by being "over" damped. Typical values range from 0.6 to 0.95. |
12 (1.0) | Extension Time | The amount of time it takes the landing gear to fully extend under normal conditions (seconds). A value of zero indicates a fixed gear. |
13 (4.0) | Retraction Time | The amount of time it takes the landing gear to fully retract under normal conditions (seconds). A value of zero indicates a fixed gear. |
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 extension becomes inhibited (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 data set takes the form "point.n=", where "n" is the index to the particular point, followed by the data.
Property | Description | Examples |
---|---|---|
point.0 to point.n |
Contact points that match the format described above. |
Mooney Bravo( point.0=1, 1.18, 0.0, -4.20, 1181.1, 0, 0.523, 33.66, 0.296, 2.5,
0.794, 3.5, 3.5, 0, 165.0, 165.0 ) |
max_number_of_points | Integer value indicating the maximum number of contact points the program will look for. | Mooney Bravo( max_number_of_points = 21 ) |
static_pitch | The static pitch of the aircraft when at rest on the ground (degrees). The program uses this value to position the aircraft at startup, in slew, and at any other time when the simulation is not actively running. | Mooney Bravo( static_pitch = 2.9 ) |
static_cg_height | The static height of the aircraft when at rest on the ground (feet). The program uses this value to position the aircraft at startup, in slew, and at any other time when the simulation is not actively running. | Mooney Bravo( static_cg_height = 3.7 ) |
gear_system_type |
This parameter defines the system type which drives the gear extension and retraction. 0 = electrical 1 = hydraulic 2 = pneumatic 3 = manual 4 = none |
Mooney Bravo( gear_system_type=0 ) DeHavilland Beaver DHC2( gear_system_type=3 ) |
emergency_extension_type |
One of: None = 0 Pump = 1 Gravity = 2 Hydraulic backup reserve = 3 (Needs [hydraulic_system] backup_reserve = 1) |
Bombardier CRJ 700( emergency_extension_type=2 ) |
tailwheel_lock | Boolean defining if a tailwheel lock is available (applicable only on tailwheel airplanes). | Gruman Goose G21A( tailwheel_lock = 1 ) |
inhibit_rudder_on_steer | Boolean which will block normal rudder input affecting landing gear steering. This could be used on aircraft which utilize only a tiller for steering on the ground. | Commercial_Airliner( inhibit_rudder_on_steer = 1 ) |
[gear_warning_system]
The following parameters define the functionality of the aircraft's gear warning system. This is generally a function of the throttle lever position and the flap deflection.
Property | Description | Examples |
---|---|---|
gear_warning_available |
Sets the type of gear warning system available on the aircraft, one of: 0 = None, 1 = Normal, 2 = Amphibian (audible alert for water vs. land setting). |
Mooney Bravo( gear_warning_available = 1 ) |
pct_throttle_limit | The throttle limit, below which the gear warning will activate if the gear is not down and locked while the flaps are deflected to at least the setting for flap_limit_idle below. This flap limit can be 0 so that the warning effectively is a function of the throttle. A value between: 0 (idle) and 1.0 (Max throttle). | Mooney Bravo( 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 will activate if the gear is not down and locked while the throttle is below the limit specified above. By setting this limit to a value greater than zero, the pilot can reduce the throttle to idle without activating the warning. This is often utilized in jets to decelerate/descend the aircraft. |
Mooney Bravo( flap_limit_idle = 0.0 ) Bombardier CRJ 700( flap_limit_idle = 15.0 ) |
flap_limit_power | The flap limit, above which the warning will activate (regardless of throttle position). |
Mooney Bravo( flap_limit_power = 16.0 ) Bombardier CRJ 700( flap_limit_power = 30.0 ) |
[brakes]
The following parameters define the aircraft's braking system:
Property | Description | Examples |
---|---|---|
parking_brake | Boolean setting if a parking brake is available on the aircraft. |
Mooney Bravo( parking_brake = 1 ) DeHavilland Beaver DHC2( parking_brake = 0 ) |
toe_brakes_scale | Sets the scaling of the braking effectiveness. 1.0 is the default. 0.0 scales the brakes to no effectiveness. | Bombardier CRJ 700( toe_brakes_scale = 1.2 ) |
auto_brakes | The number of increments that the auto-braking switch can be turned to. | Bombardier CRJ 700( auto_brakes = 0 ) |
hydraulic_system_scalar | The ratio of hydraulic system pressure to maximum brake hydraulic pressure. | Bombardier CRJ 700( hydraulic_system_scalar = 1 ) |
differential_braking_scale | Differential braking is a function of the normal both brakes on and the rudder pedal input. The amount of difference between the left and right brake is scaled by this value. 1.0 is the normal setting if differential braking is desired (particularly on tailwheel airplanes). 0.0 is the setting if no differential braking is desired. | Piper Cub( differential_braking_scale = 1.0 ) |
parking_brake_linked_to_toe_brakes | By default, the parking brake will release upon application of toe brakes. If this is not desired, setting this to 0 will prevent this behavior. | parking_brake_linked_to_toe_brakes = 0 |
[ClampingOnGround]
Clamping on the ground occurs when the aircraft speed, acceleration, and power are below given thresholds. Clamping prevents extremely small jitter and/or movement that can occur on some aircraft. This movement is generally so small that it is not obvious in most circumstances.
The following thresholds must all be met to switch clampong on/off:Property | Description | Examples |
---|---|---|
MinVelocity | The minimum speed relative to the ground (feet per second). |
Sikorsky UH-60M Battlehawk( MinVelocity = 0.2 ) |
MinAcceleration | The minimum total acceleration in the body axis (feet per second squared). |
Sikorsky UH-60M Battlehawk( MinAcceleration = 1.4 ) |
MinRotationAcceleration | The minimum total rotational acceleration in the body axis (radians per second squared). |
Sikorsky UH-60M Battlehawk( MinRotationAcceleration = 1.0 ) |
MinPower |
Airplanes: The throttle position (0.0 - 1.0). Helicopters: The thrust / weight ratio. |
Sikorsky UH-60M Battlehawk( MinPower = 0.09 ) |
[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. |
Bombardier CRJ 700( normal_pressure = 3000.0 ) DeHavilland Beaver DHC2( normal_pressure = 1000.0 ) |
electric_pumps | The number of electric hydraulic pumps the aircraft is configured with. |
Bombardier CRJ 700( electric_pumps = 1 ) |
engine_map | This array of positive integers sets the number of hydraulic pumps on the corresponding engines of the aircraft. The values correspond to the order of the engines, starting with the left-most engine first and moving right. By default, all engines are not equipped with any hydraulic pumps. | DeHavilland Beaver DHC2( engine_map = 1 ) |
backup_reserve | This system includes a backup reservoir for use after primary pumps have failed. | ( backup_reserve = 1 ) |
max_reservoir_pressure_efficiency | The approximate level in which the pumps will maintain the reservoir level. Set to 1.0 if a perfect system is desired. | ( max_reservoir_pressure_efficiency = 0.98 ) |
min_pct_rpm_for_max_pressure | The percentage of maximum engine RPM that engine driven hydraulic pumps will achieve 100% of normal pressure. The pressure will ramp up linearly. Omission of this constant will result in use of an internal mapping of RPM to pressure. | ( min_pct_rpm_for_max_pressure = 0.2 ) |
[views]
The following parameter define the pilot's viewpoint.
Property | Description | Examples |
---|---|---|
eyepoint | Position relative to datum reference point. | Mooney Bravo( eyepoint = -4.52, -0.884, 1.4 ) |
zoom | Zoom the view in or out from the viewpoint. | Default( 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] sections contained in the aircraft.cfg file.
Property | Description | Examples |
---|---|---|
type |
Integer value that indicates if this is a leading edge or trailing edge flap set: 0 = no flaps 1 = trailing edge, 2 = leading edge. |
Mooney Bravo( type = 1 ) |
span-outboard | The percentage of half-wing span the flap extends to (from the wing-fuselage intersection). |
Mooney Bravo( span-outboard = 0.5 ) Bombardier CRJ 700( span-outboard = 0.8 ) |
extending-time | Time it takes for the flap set to extend to the fullest deflection angle specified (seconds). |
Mooney Bravo( extending-time = 5 ) |
flaps-position.0 to flaps-position.n |
Each element of the flaps-position array indicates the deflection angle to which the flaps will deflect (in degrees). The largest deflection angle will be the one used for full flap deflection. |
Maule M7 260C( flaps-position.0 = -7 ) |
damaging-speed | Speed at which the flaps begin to accrue damage (Knots Indicated Airspeed, KIAS). |
Mooney Bravo( damaging-speed = 250 ) |
blowout-speed | Speed at which the flaps depart the aircraft (Knots Indicated Airspeed, KIAS). |
Mooney Bravo( blowout-speed = 300 ) |
lift_scalar | The percentage of total lift due to flap deflection that this flap set is responsible for at full deflection. | Mooney Bravo( lift_scalar = 1.0 ) |
drag_scalar | The percentage of total drag due to flap deflection that this flap set is responsible for at full deflection. |
Mooney Bravo( drag_scalar = 1.0 ) |
pitch_scalar | The percentage of total pitch due to flap deflection that this flap set is responsible for at full deflection. | Mooney Bravo( pitch_scalar= 1.0 ) |
system_type |
Integer value that indicates what type of system drives the flaps to deflect:, one
of: 0 = Electric 1 = Hydraulic 2 = Pneumatic 3 = Manual 4 = None |
Mooney Bravo( system_type = 1 ) |
[radios]
There should be a radio section in each aircraft.cfg. This section configures the radios for each individual aircraft. Each of the following keywords has a flag or set of flags, that determine if the particular radio element is available in 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. | Mooney Bravo( Audio.1 = 1 ) |
com.1 | Two flags, set the first one to 1 if a Com1 radio is available, and the second if it supports a standby frequency. |
Mooney Bravo( Com.1 = 1, 1 ) |
com.2 | Two flags, set the first one to 1 if a Com2 radio is available, and the second if it supports a standby frequency. You cannot have Com2 without Com1. |
Mooney Bravo( Com.2 = 1, 1 ) |
nav.1 | Three flags, set the first to 1 if there is a Nav1 receiver, the second if it supports a standby frequency, and the third if it supports a glideslope indication. |
Mooney Bravo( Nav.1 = 1, 1, 1 ) |
nav.2 | Three flags, set the first to 1 if there is a Nav2 receiver, the second if it supports a standby frequency, and the third if it supports a glideslope indication. You cannot have Nav2 without Nav1. |
Mooney Bravo( Nav.2 = 1, 1, 0 ) |
adf.1 | If there is an ADF receiver, set to 1. |
Mooney Bravo( Adf.1 = 1 ) |
adf.2 | If there is an ADF2 receiver, set to 1. | Bombardier CRJ 700( Adf.2 = 1 ) |
tacan.1 | Two flags, set the first to 1 if there is a Tacan 1 receiver and the second if it supports a standby frequency. |
Tacan.1 = 1, 1, 0 |
tacan.2 | Two flags, set the first to 1 if there is a Tacan 2 receiver and the second if it supports a standby frequency. You cannot have Tacan2 without Tacan1. |
Tacan.2 = 1, 1, 0 |
transponder.1 | If there is a transponder, set to 1. |
Mooney Bravo( Transponder.1 = 1 ) |
marker.1 | If there is a marker beacon receiver, set to 1. |
Mooney Bravo( Marker.1 = 1 ) |
ComFrequencyRange | Sets the min and max frequency, in MHz, in which the aircraft's COM radios are limited. 118 - 137 is the default range. |
ComFrequencyRange = 118.000,137.000 |
[lights]
Each light that requires a special effect should be entered in this section. The following table gives the codes for the switches 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 |
11 | General |
12 | Headlight |
13 | Brake |
Property | Description | Examples |
---|---|---|
light.0 to light.n |
The first entry of the line defines which circuit, or switch, the light is connected to (see the code table above). Multiple lights may be connected to a single switch. The next three entries are the position relative to datum reference point. The final entry is the special effect file name that is triggered (for example, fx_navred). These files have .fx extensions and should be placed in the root effects folder. |
Mooney Bravo( light.0 = 3, -2.65, -18.25, -0.18, fx_navred , ) Bombardier CRJ 700( light.0 = 3, -64.70, -37.00, -0.50, fx_navredm , ) Bombardier CRJ 700( light.1 = 3, -64.70, 37.00, -0.50, fx_navgrem , ) Bombardier CRJ 700( light.2 = 3, -104.63, 0.00, 14.30, fx_navwhi , ) Bombardier CRJ 700( light.3 = 1, -29.00, 0.00, -2.30, fx_beaconb , ) |
[keyboard_response]
The aircraft flight controls can be manipulated by the keyboard. Because flight controls naturally become more sensitive as airspeed increases, it can become quite difficult to control the aircraft via the keyboard at high speeds. To address this problem, the amount a single keypress increments a flight control is decreased by a factor of 1/2 at the first airspeed (in knots) listed on the line for the control, and to 1/8 at the second airspeed, and to a scale interpolated from these values for all airspeeds in between. The example below shows that an elevator will increment by one degree when the airspeed is zero, by ¾ of one degree at 50 knots, ½ of one degree at 100 knots, 5/16 of one degree at 140 knots, and 1/8 of one degree at 180 knots or greater speed.
Property | Description | Examples |
---|---|---|
elevator | Two breakpoint speeds for keypress increments. |
Mooney Bravo( elevator = 100, 180 ) |
aileron | Two breakpoint speeds for keypress increments. |
Mooney Bravo( aileron = 200, 1000 ) |
rudder | Two breakpoint speeds for keypress increments. |
Mooney Bravo( rudder = 200, 1000 ) |
[direction_indicators]
This section is used to define the characteristics of the direction indicators on the instrument panels, but does not include the magnetic compass (which has a separate section). The list of indicators should be listed in order: 0,1,2,…n.
Property | Description | Examples |
---|---|---|
direction_indicator.0 to direction_indicator.n |
One or two codes. If the indicator is type 4, then there must be two entries here
(the indicator, and the indicator to which 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 |
Mooney Bravo( direction_indicator.0=1,0 ) |
induction_compass.0 to induction_compass.n |
If there is an induction compass, one of: 1 = Electric 2 = Anemometer driven |
[attitude_indicators]
This section is used to define the characteristics of the attitude indicators on the instrument panels. The list of indicators should be listed 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 |
Mooney Bravo( attitude_indicator.0 = 1 ) |
[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. |
Mooney Bravo( altimeter.0=1 ) Mooney Bravo( altimeter.1=1 ) |
[turn_indicators]
This section is used to define the characteristics of the turn indicators on the instrument panels. The list of indicators should be listed in order: 0,1,2,…n.
Property | Description | Examples |
---|---|---|
turn_indicator.0 |
Two code values, which define the system on which the turn indicators are dependent.
The first value is for turn, the second for bank. The codes are: 0 = None 1 = Electrically driven gyro 2 = Vacuum driven gyro |
DeHavilland Beaver DHC2( turn_indicator.0=1 ) |
[vacuum_system]
The following parameters define the aircraft's vacuum system:
Property | Description | Examples |
---|---|---|
max_pressure | Maximum pressure in psi. |
Mooney Bravo( max_pressure=5.15 ) |
vacuum_type |
Vacuum type, one of: 0 = None 1 = Engine pump (default) 2 = Pneumatic 3 = Venturi. |
Mooney Bravo( vacuum_type=1 ) |
electric_backup_pressure | Backup pressure in psi. | Mooney Bravo( electric_backup_pressure=4.9 ) |
engine_map | This series of flags sets whether the corresponding engines of the aircraft are configured with vacuum systems. The flags correspond in order of the engines, starting with the left-most engine first and moving right. |
Mooney Bravo( engine_map=1 ) Bombardier CRJ 700( engine_map=1,1 ) |
[pneumatic_system]
The following parameters define the aircraft's pneumatic pressure system:
Property | Description | Examples |
---|---|---|
max_pressure | The maximum pressure of the pneumatic system. | Piper Cub( max_pressure=0 ) |
bleed_air_scalar | The ratio of bleed-air pressure from the engines to pneumatic air pressure in the pneumatic system. |
Bombardier CRJ 700( bleed_air_scalar=1.00000 ) |
[exits]
The following parameters define the aircraft's exits:
Property | Description | Examples |
---|---|---|
number_of_exits | This value defines the number of simulated exits, or doors, on the aircraft. |
Bombardier CRJ 700( number_of_exits = 3 ) |
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 of exit, one of: 0 = Main 1 = Cargo 2 = Emergency |
Bombardier CRJ 700( exit.0 = 0.4, -16.50, -4.5, 0.5, 0 ) Bombardier CRJ 700( exit.1 = 0.4, -74.00, -4.5, 0.5, 1 ) Bombardier CRJ 700( 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 all aircraft.
Each entry can be followed by a 1 if the effect is to be run for a single iteration. Set this number to zero or leave blank (the default), for the effect to continue as long as the respective action 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 | Mooney Bravo( wake=fx_wake ) |
water | The landing, taxiing or taking off from water effect. | fx_spray | False | Mooney Bravo( water=fx_spray ) |
waterspeed | Traveling at speed on the water. | fx_spray | False | |
dirt | Moving on dirt. | fx_tchdrt | False | Mooney Bravo( dirt=fx_tchdrt ) |
concrete | Moving on concrete. | fx_sparks | False | Mooney Bravo( concrete=fx_sparks ) |
touchdown | The touchdown effect, which usually is followed by an optional 1 to indicate the effect is to be run once only. | fx_tchdwn | True |
Mooney Bravo( touchdown=fx_tchdwn_s, 1 ) |
contrail | Contrail effect, applies to jets flying above 29000ft. | fx_contrail_l | False | |
startup | Engine startup. | fx_engstrt | True | Piper Cub( 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 | |
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 | Maule M7 260C Ski paint1( SnowTrack = fx_snowtrack ) |
WheelSnowSpray | Taking off on snow. | fx_WheelSnowSpray | False | Maule M7 260C Ski paint1( WheelSnowSpray = fx_WheelSnowSpray ) |
WheelWetSpray | Taking off on wet runway. | fx_WheelWetSpray | False | Maule M7 260C Ski paint1( 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 | |
Killed | When health points drop below 0, the object is determined to be killed. An effect such as smoke or fire is most typically played. This effect is only applied when the object is in the air. | fx_FlamingDebris | False | |
KilledGround | When health points drop below 0, the object is determined to be killed. An effect such as smoke or fire is most typically played. This effect is only applied when the object is on the ground. | fx_FlamingDebrisGround | False | |
windshield_rain_effect_available | Special case, set this to 0 to turn off the effect of rain on the windshield. |
[autopilot]
The following parameters determine the functionality of the aircraft's autopilot system, including the flight director.
Navigation Modes:
The navigation and glideslope controllers utilize standard proportional/integral /derivative feedback controllers (PID). The integrator and derivative controllers have boundaries, which are the maximum error from the controlled parameter in which these are active. It is not necessary to have all three components active. Setting the respective control constant to 0 effectively disables that component, allowing PI or PD controllers to be 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. | Mooney Bravo( autopilot_available=1 ) |
flight_director_available | Setting this flag to a 1 makes available a flight director on the aircraft. |
Mooney Bravo( flight_director_available=1 ) |
default_vertical_speed | The default vertical speed, in feet per second, that the autopilot will command when selecting a large altitude change. |
Mooney Bravo( default_vertical_speed= 700.0 ) Bombardier CRJ 700( default_vertical_speed= 1800.0 ) |
autothrottle_available |
Setting this flag to a 1 makes available an autothrottle system on the aircraft.
Note: Not applicable to helicopters. |
Mooney Bravo( autothrottle_available = 0 ) Bombardier CRJ 700( autothrottle_available = 1 ) |
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.
Note: Not applicaple to helicopters. |
Bombardier CRJ 700( autothrottle_arming_required= 0 ) |
autothrottle_max_rpm |
This sets the maximum engine speed, in percent, that the autothrottle will attempt
to maintain.
Note: Not applicaple to helicopters. |
Bombardier CRJ 700( autothrottle_max_rpm = 90 ) |
autothrottle_takeoff_ga |
Setting this flag to 1 enables takeoff / go-around operations with the autothrottle.
Note: Not applicaple to helicopters. |
Bombardier CRJ 700( autothrottle_takeoff_ga= 0 ) |
helo_airspeed_hold |
For helicopters only, setting this flag to 1 enables airspeed hold capability.
Note: Not applicaple to airplanes. |
|
default_pitch_mode |
This determines the default pitch mode when the autopilot logic is turned on. 0 = None 1 = Pitch Hold (Airplane: current pitch angle, Helicopter: pitch stability mode). 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.
Note: Not applicaple to helicopters. |
Mooney Bravo( pitch_takeoff_ga=8.0 ) Bombardier CRJ 700( pitch_takeoff_ga=8.0 ) |
max_pitch | The maximum pitch angle in degrees that the autopilot will command either up or down. |
Mooney Bravo( 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.
Note: Not applicaple to helicopters. |
Mooney Bravo( 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.
Note: Not applicaple to helicopters. |
Mooney Bravo( 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.
Note: Not applicaple to helicopters. |
Mooney Bravo( 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.
Note: Not applicaple to helicopters. |
Mooney Bravo( 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.
Note: Not applicaple to helicopters. |
Mooney Bravo( 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. |
Bombardier CRJ 700( max_bank=30,15 ) |
max_bank_acceleration |
The maximum angular bank acceleration, in degrees per second squared, that the autopilot
will command left or right.
Note: Not applicaple to helicopters. |
Mooney Bravo( 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.
Note: Not applicaple to helicopters. |
Mooney Bravo( max_bank_velocity=3.00 ) |
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.
Note: Not applicaple to helicopters. |
Mooney Bravo( max_throttle_rate=0.10 ) |
nav_proportional_control | Proportional controller constant in lateral navigation modes. |
Mooney Bravo( nav_proportional_control=9.00 ) Bombardier CRJ 700( nav_proportional_control=11.00 ) |
nav_integrator_control | Integral controller constant in lateral navigation modes. | Bombardier CRJ 700( nav_integrator_control=0.20 ) |
nav_derivative_control | Derivative controller constant in lateral navigation modes. | Mooney Bravo( nav_derivative_control=0.00 ) |
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. |
Mooney Bravo( 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. |
Mooney Bravo( nav_derivative_boundary=0.00 ) |
gs_proportional_control | Proportional controller constant in glideslope mode. |
Mooney Bravo( gs_proportional_control=9.52 ) Bombardier CRJ 700( gs_proportional_control=9.52 ) |
gs_integrator_control | Integral controller constant in glideslope mode. |
Mooney Bravo( gs_integrator_control=0.26 ) Bombardier CRJ 700( gs_integrator_control=0.26 ) |
gs_derivative_control | Derivative controller constant in glideslope mode. | |
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_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. | |
yaw_damper_gain | The proportional gain on the yaw dampers yaw rate error. |
Mooney Bravo( yaw_damper_gain = 0.0 ) Bombardier CRJ 700( yaw_damper_gain = 1.0 ) |
direction_indicator |
Indicates which direction indicator system on the aircraft is being referenced by
the autopilot. 0 = the first, and is the default. |
|
attitude_indicator |
Indicates which attitude indicator system on the aircraft is being referenced by
the autopilot. 0 = the first, and is the default. |
|
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). 3 = Bank Hold (Airplane: current bank angle, Helicopter: roll stability mode). If no value is set, Wing Level Hold will be the default. |
Miscellaneous default AP modes:
The following flags are legacy, and were enabled to allow aircraft to be configured with no pitch and/or bank modes. While these flags are still supported, the preferred flags are included above in the respective vertical and lateral sections.
Property | Description | Examples |
use_no_default_pitch |
Setting this flag to 1 will cause the default pitch mode to be "None". It will actually
set the variable default_pitch_mode to zero, so that there is no default pitch mode
when the autopilot logic is activated. The preferred method is to test the default_bank_mode directly. |
See examples for default_bank_mode |
[fuel]
This section defines the characteristics of the fuel system, including the tanks, fuel type, and the number of fuel selectors. The number of fuel selectors is intended to match the number of visual selectors 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. |
Bombardier CRJ 700( Center1 = -48.7, 0.0, -4.0, 982.0, 0.0 ) DeHavilland Beaver DHC2( Center3=-10.600000,0.000000,-1.900000,25.000000,0.000000 ) Mooney Bravo( RightMain = -4.1, 7.9, -0.8, 47.5, 3.0 ) Maule M7 260C( LeftAux = -2.24, -11.4, 2.40, 15.0, 0.00 ) |
fuel_type |
One of: 1 = Avgas 2 = JetA |
Mooney Bravo( fuel_type = 1 ) Bombardier CRJ 700( fuel_type = 2 ) |
number_of_tank_selectors | Number of fuel tank selectors (maximum 4 and should be less than or equal to the number of engines). |
Mooney Bravo( number_of_tank_selectors = 1 ) Bombardier CRJ 700( number_of_tank_selectors = 1 ) |
electric_pump | Boolean that sets whether an electric boost pump is available, 0 = FALSE, 1 = TRUE. | Mooney Bravo( electric_pump = 1 ) |
fuel_dump_rate | Percent of fuel that can be dumped per second. | |
engine_driven_pump | Set to 0 if the pump is engine driven (1 is the default). | DeHavilland Beaver DHC2( engine_driven_pump=1 ) |
manual_pump | Set to 1 if there is a manual transfer pump. | DeHavilland Beaver DHC2( manual_transfer_pump=1 ) |
anemometer_pump | Set to 1 if there is an anemometer pump. | |
default_leak_rate_gps | Allows overriding the default maximum rate (gallons per second) when a fuel leak is selected. | default_leak_rate_gps = 0.2 |
[airplane_geometry]
This section has been added mainly for reference. Although you can edit these values by hand here in the aircraft.cfg file, modification of some of these variables will have little to no effect on airplane performance, as the flight model aerodynamic coefficients are all located in the .air file.
Property | Description | Examples |
---|---|---|
wing_area | Area of the top surface of the entire wing tip-to-tip (ft2). |
Mooney Bravo( wing_area = 175.0 ) Bombardier CRJ 700( wing_area = 738.7 ) |
wing_span | Wing span is the horizontal distance from wing-tip to wing-tip (feet). |
Mooney Bravo( wing_span = 36.1 ) Bombardier CRJ 700( wing_span = 76.25 ) |
wing_root_chord | Length of the wing chord (leading edge to trailing edge) at the intersection of the wing and the fuselage (feet). |
Mooney Bravo( wing_root_chord = 5.1 ) Bombardier CRJ 700( wing_root_chord = 17.3 ) |
wing_dihedral | When looking at the front of an aircraft, this is the angle between the wing leading edge and a horizontal line parallel to the ground (degrees). |
Mooney Bravo( wing_dihedral = 5.5 ) Bombardier CRJ 700( wing_dihedral = 0.0 ) |
wing_incidence | When looking at the side of an aircraft from the wing tip, this is the angle the mean wing chord makes with a horizontal line parallel to the ground, (degrees). Note: this parameter is not used in the real-time aerodynamic calculations, as it is already factored into the lift and drag parameters. | Mooney Bravo( wing_incidence = 2.5 ) |
wing_twist | This is the difference in wing incidence from the root chord and the tip chord of the wing, (degrees). Also known as wash-out. |
Mooney Bravo( wing_twist = -1.5 ) Bombardier CRJ 700( wing_twist = -1.0 ) |
oswald_efficiency_factor | This is a measure of the aerodynamic efficiency of the wing. A theoretically perfect wing will have a factor of 1.0. |
Mooney Bravo( oswald_efficiency_factor= 0.6 ) Bombardier CRJ 700( oswald_efficiency_factor= 0.8 ) |
wing_winglets_flag | Boolean to indicate if the aircraft incorporates the use of winglets; 0 = FALSE, 1 = TRUE. | Mooney Bravo( wing_winglets_flag= 0 ) |
wing_sweep | When looking down on top of an aircraft, this is the angle the wing leading edge makes with a horizontal line perpendicular to the fuselage, (degrees). |
Mooney Bravo( wing_sweep = 0.0 ) Bombardier CRJ 700( wing_sweep = 27.0 ) |
wing_pos_apex_lon | Longitudinal distance of the wing apex (measured at centerline of aircraft) from defined reference point (feet). This distance is measured positive in the forward (out the aircraft nose) direction. |
Mooney Bravo( wing_pos_apex_lon = -2.6 ) Bombardier CRJ 700( wing_pos_apex_lon = -42.2 ) |
wing_pos_apex_vert | Vertical distance of the wing apex (measured at centerline of aircraft) from defined reference point (feet). This distance is measured positive in the up direction. | Bombardier CRJ 700( wing_pos_apex_vert = -3.6 ) |
htail_area | Area of the top surface of the entire horizontal tail (tip-to-tip) (ft2). |
Mooney Bravo( htail_area = 34.0 ) Bombardier CRJ 700( htail_area = 192.0 ) |
htail_span | Horizontal tail span is the horizontal distance from horizontal tail-tip to horizontal tail -tip (feet). |
Mooney Bravo( htail_span = 11.8 ) Bombardier CRJ 700( htail_span = 14.4 ) |
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 the aircraft nose) direction. |
Mooney Bravo( htail_pos_lon = -18.6 ) Bombardier CRJ 700( htail_pos_lon = -95.9 ) |
htail_pos_vert | Vertical distance of the horizontal tail apex (measured at centerline of aircraft) from defined reference point, (feet). This distance is measured positive in the up direction. |
Bombardier CRJ 700( htail_pos_vert = 12.7 ) DeHavilland Beaver DHC2( htail_pos_vert = 0.9 ) |
htail_incidence | When looking at the side of an aircraft from the horizontal tail tip, this is the angle the mean horizontal tail chord makes with a horizontal line parallel to the ground (degrees). |
Mooney Bravo( htail_incidence = 1.0 ) Bombardier CRJ 700( htail_incidence = 4.0 ) |
htail_sweep | When looking down on top of an aircraft, this is the angle the horizontal tail leading edge makes with a horizontal line perpendicular to the fuselage (degrees). |
Mooney Bravo( htail_sweep = 0.0 ) Bombardier CRJ 700( htail_sweep = 35.0 ) |
vtail_area | Area of the surface of one side of the vertical tail (fuselage-to-tip) (ft2). |
Mooney Bravo( vtail_area = 10.0 ) Bombardier CRJ 700( vtail_area = 108.0 ) |
vtail_span | Vertical tail span is the vertical distance from the vertical tail-fuselage intersection to the tip of the vertical tail (feet). |
Mooney Bravo( vtail_span = 3.6 ) Bombardier CRJ 700( vtail_span = 11.6 ) |
vtail_sweep | When looking at the side of the vertical tail, this is the angle the vertical tail leading edge makes with a vertical line perpendicular to the fuselage (degrees). |
Mooney Bravo( vtail_sweep = 0.0 ) Bombardier CRJ 700( vtail_sweep = 44.0 ) |
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 the aircraft nose) direction. |
Mooney Bravo( vtail_pos_lon = -16.5 ) Bombardier CRJ 700( vtail_pos_lon = -86.7 ) |
vtail_pos_vert | Vertical distance of the vertical tail apex (measured at centerline of aircraft) from defined reference point (feet). This distance is measured positive in the up direction. |
Mooney Bravo( vtail_pos_vert = 1.5 ) Bombardier CRJ 700( vtail_pos_vert = 3.7 ) |
elevator_area | Area of the top surface of the entire elevator (tip-to-tip) (ft2). |
Mooney Bravo( elevator_area = 16.6 ) Bombardier CRJ 700( elevator_area = 42.1 ) |
aileron_area | Area of the top surface of all the ailerons on the wing (ft2). |
Mooney Bravo( aileron_area = 18.3 ) Bombardier CRJ 700( aileron_area = 22.0 ) |
rudder_area | Area of the side surface of the entire rudder (ft2). |
Mooney Bravo( rudder_area = 6.7 ) Bombardier CRJ 700( rudder_area = 21.4 ) |
elevator_up_limit | Angular limit of the elevator when deflected up (degrees). | Mooney Bravo( elevator_up_limit = 28.0 ) |
elevator_down_limit | Angular limit of the elevator when deflected down (degrees). |
Mooney Bravo( elevator_down_limit = 21.0 ) Bombardier CRJ 700( elevator_down_limit = 20.0 ) |
aileron_up_limit | Angular limit of the aileron when deflected up (degrees). |
Mooney Bravo( aileron_up_limit = 20.0 ) Bombardier CRJ 700( aileron_up_limit = 18.0 ) |
aileron_down_limit | Angular limit of the aileron when deflected down (degrees). |
Mooney Bravo( aileron_down_limit = 15.0 ) Bombardier CRJ 700( aileron_down_limit = 18.0 ) |
rudder_limit | Angular limit of the rudder deflection (degrees). |
Mooney Bravo( rudder_limit = 24.0 ) Bombardier CRJ 700( rudder_limit = 30.0 ) |
elevator_trim_limit | Angular limit of the elevator trim tab (degrees). |
Mooney Bravo( elevator_trim_limit = 19.5 ) Bombardier CRJ 700( 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. |
Mooney Bravo( spoiler_limit = 90.0 ) Bombardier CRJ 700( spoiler_limit = 60.0 ) |
spoiler_extension_time | Spoiler extension time in seconds. | Mooney Bravo( spoiler_extension_time = 0.25 ) |
spoilerons_available | Boolean to indicate if the spoilers also behave as spoilerons for roll control (if spoilers are available): 0 = FALSE, 1 = TRUE. |
Mooney Bravo( spoilerons_available = 0 ) Bombardier CRJ 700( spoilerons_available = 1 ) |
aileron_to_spoileron_gain | If spoilerons are available, this value is the constant used in determining the amount of spoiler deflection per aileron deflection. |
Mooney Bravo( aileron_to_spoileron_gain = 0 ) Bombardier CRJ 700( aileron_to_spoileron_gain = 4.6 ) |
min_ailerons_for_spoilerons | This value indicates at what aileron deflection the spoilers are become active for roll control, (degrees). |
Mooney Bravo( min_ailerons_for_spoilerons = 0 ) Bombardier CRJ 700( min_ailerons_for_spoilerons = 5 ) |
min_flaps_for_spoilerons | This value indicates at what minimum flap handle position the spoilerons become active. | Bombardier CRJ 700( min_flaps_for_spoilerons= 0.0 ) |
auto_spoiler_available | Set to 1 if auto spoiler is available. |
Mooney Bravo( auto_spoiler_available = 0 ) Bombardier CRJ 700( auto_spoiler_available = 1 ) |
spoiler_system_type |
Integer value that indicates what type of system drives the spoilers to deflect.
One of: 0 = Electric 1 = Hydraulic 2 = Pneumatic 3 = Manual 4 = None |
( spoiler_system_type = 1 ) |
positive_g_limit_flaps_up | Design g load tolerance (flaps up). |
Mooney Bravo( positive_g_limit_flaps_up = 4.0 ) Bombardier CRJ 700( positive_g_limit_flaps_up = 3.0 ) |
positive_g_limit_flaps_down | Design g load tolerance (flaps down). |
Mooney Bravo( positive_g_limit_flaps_down=2.000000 ) |
negative_g_limit_flaps_up | Design g load tolerance (negative, flaps up). |
Mooney Bravo( negative_g_limit_flaps_up = -1.5 ) Bombardier CRJ 700( negative_g_limit_flaps_up = -2.0 ) |
negative_g_limit_flaps_down | Design g load tolerance (negative, flaps down). |
Mooney Bravo( negative_g_limit_flaps_down= -1.5 ) |
load_safety_factor | Design g load safety factor. | Mooney Bravo( load_safety_factor = 1.5 ) |
fly_by_wire | Fly by wire system available. | |
spoiler_handle_available | Boolean that configures the airplane with manual control of the spoiler deflections. 0 = FALSE, 1 = TRUE. | |
flap_to_aileron_scale | Flaperons - deflection of ailerons due to flap deflection. |
DeHavilland Beaver DHC2( flap_to_aileron_scale = 0.3 ) |
aileron_to_rudder_scale | Link the rudder to aileron input. | |
elevator_hydraulic_boost_percent | Specifies the percentage of aileron deflection (0.0 - 1.0) dependent on hydraulic pressure. For example, a value of 0.8 (80%) would mean that only 0.2 (20%) deflection would be possible with no hydraulic pressure. The default value is 0.0, no hydraulic dependency. | aileron_hydraulic_boost_percent=0.8 |
rudder_hydraulic_boost_percent | Specifies the percentage of rudder deflection (0.0 - 1.0) dependent on hydraulic pressure. For example, a value of 0.8 (80%) would mean that only 0.2 (20%) deflection would be possible with no hydraulic pressure. The default value is 0.0, no hydraulic dependency. | rudder_hydraulic_boost_percent=0.8 |
[reference speeds]
The values given in this section are mainly for reference, as the 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). |
Mooney Bravo( flaps_up_stall_speed = 66.0 ) Bombardier CRJ 700( flaps_up_stall_speed = 112.0 ) |
full_flaps_stall_speed | Stall speed of the aircraft in a dirty (flaps full down) configuration at standard sea level conditions, (Knots True Airspeed, KTAS). |
Mooney Bravo( full_flaps_stall_speed = 52.8 ) Bombardier CRJ 700( full_flaps_stall_speed = 102.0 ) |
cruise_speed | Typical cruise speed of the aircraft in a clean (flaps up) configuration at a typical cruise altitude, (Knots True Airspeed, KTAS). |
Mooney Bravo( cruise_speed = 180.0 ) Bombardier CRJ 700( cruise_speed = 473.0 ) |
max_mach | Maximum design mach of the aircraft. This generally only applies to turbine airplanes. | Bombardier CRJ 700( max_mach = 0.83 ) |
max_indicated_speed | Maximum design indicated airspeed. Also referred to as Never Exceed Speed or Red Line of the aircraft, (Knots Indicated Airspeed). |
Mooney Bravo( max_indicated_speed = 195 ) Bombardier CRJ 700( max_indicated_speed = 335.0 ) |
[forcefeedback]
As detailed in the tables below, the parameters in this section of an aircraft.cfg file define the forces generated by that aircraft if the user is operating a force feedback joystick.
Stick shaker parameters
These parameters define the simulated stick shaker force felt in the stick or yoke when flying an aircraft equipped with a stick shaker (such as the Learjet 45).
Gear bump parameters
These parameters define the simulated forces transferred from the airframe and gear drag to the stick or yoke when the aircraft's nose and main landing gear is raised or lowered (cycled). In fixed-gear aircraft this effect won't be felt because, by definition, the landing gear doesn't move. Different aircraft have different gear geometries that result in each of the gear mechanisms starting and ending its cycle at a different time. The timing deltas are brief, typically less than a second between the time that each gear starts and ends its cycle.
Ground bumps parameters
These parameters collectively define a composite force that simulates the forces felt through an aircraft's ground steering controls as the aircraft travels over an uneven surface. The parameters are divided into two subgroups (numbered 1 and 2), and define the behavior of two distinct forces. The combination of the two forces define a composite force that is transferred to the stick or yoke. The two forces are both sinusoidal periodic forces, with frequencies determined by 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 the force is felt.
Crash parameters
These parameters define the simulated forces felt in the stick or yoke when the aircraft crashes. The parameters are divided into two subgroups (numbered 1 and 2), and define the behavior of two distinct crash-induced forces. The first force is a constant force that lasts for 0.5 seconds. After 0.5 seconds, it stops and the second force starts. The second force is a periodic square wave force; its amplitude declines linearly to 0.
Property | Description | Examples |
---|---|---|
gear_bump_nose_magnitude | Integer from 0 - 10000. |
Mooney Bravo( gear_bump_nose_magnitude=3000 ) |
gear_bump_nose_direction | Integer from 0 - 35999 degrees. | Mooney Bravo( gear_bump_nose_direction=18000 ) |
gear_bump_nose_duration | Integer, microseconds. | Mooney Bravo( gear_bump_nose_duration=250000 ) |
gear_bump_left_magnitude | Integer from 0 - 10000. |
Mooney Bravo( gear_bump_left_magnitude=2700 ) |
gear_bump_left_direction | Integer from 0 - 35999 degrees. |
Mooney Bravo( gear_bump_left_direction=35500 ) Bombardier CRJ 700( gear_bump_left_direction=9000 ) |
gear_bump_left_duration | Integer, microseconds. | Mooney Bravo( gear_bump_left_duration=250000 ) |
gear_bump_right_magnitude | Integer from 0 - 10000. |
Mooney Bravo( gear_bump_right_magnitude=2700 ) |
gear_bump_right_direction | Integer from 0 - 35999 degrees. |
Mooney Bravo( gear_bump_right_direction=00500 ) Bombardier CRJ 700( gear_bump_right_direction=27000 ) |
gear_bump_right_duration | Integer, microseconds. | Mooney Bravo( gear_bump_right_duration=250000 ) |
ground_bumps_magnitude1 | Integer from 0 - 10000. |
Mooney Bravo( ground_bumps_magnitude1=1300 ) |
ground_bumps_angle1 | Integer from 0 - 35999 degrees. | Mooney Bravo( ground_bumps_angle1=8900 ) |
ground_bumps_intercept1 | Floating point number, from 0 to 1,000,000 cycles per second. |
Mooney Bravo( ground_bumps_intercept1=3.0 ) |
ground_bumps_slope1 | Floating point number, from 0 to 1,000,000 cycles per second. |
Mooney Bravo( ground_bumps_slope1=0.20 ) |
ground_bumps_magnitude2 | Integer from 0 - 10000. |
Mooney Bravo( ground_bumps_magnitude2=200 ) |
ground_bumps_angle2 | 0 - 35999 degrees. |
Mooney Bravo( ground_bumps_angle2=09100 ) |
ground_bumps_intercept2 | Floating point number, from 0 to 1,000,000 cycles per second. |
Bombardier CRJ 700( ground_bumps_intercept2 =1.075 ) |
ground_bumps_slope2 | Floating point number, from 0 to 1,000,000 cycles per second. |
Mooney Bravo( ground_bumps_slope2=0.035 ) |
crash_magnitude1 | Sets the magnitude of the first force, from 0 to 10000. | Mooney Bravo( crash_magnitude1=10000 ) |
crash_direction1 | Sets the direction from which first force is felt, from 0 to 35999. | Mooney Bravo( crash_direction1=01000 ) |
crash_magnitude2 | Sets the initial magnitude of the second force, from 0 to 10000. | Mooney Bravo( crash_magnitude2=10000 ) |
crash_direction2 | Sets the direction from which the second force is felt, from 0 to 35999. | Mooney Bravo( crash_direction2=9000 ) |
crash_period2 | Determines the frequency (frequency = 1/period) of the second crash force, in microseconds. | Mooney Bravo( crash_period2=75000 ) |
crash_duration2 | Sets the amount of time that the second crash force is felt, in microseconds. | Mooney Bravo( crash_duration2=2500000 ) |
stick_shaker_magnitude | Integer from 0 - 10000. | Bombardier CRJ 700( stick_shaker_magnitude=5000 ) |
stick_shaker_direction | Integer from 0 - 35999 degrees. | Bombardier CRJ 700( stick_shaker_direction=0 ) |
stick_shaker_period | In microseconds. | Bombardier CRJ 700( 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 |
Mooney Bravo( type=2 ) |
stick_shaker | Set to 1 if the aircraft has a stick shaker. | Mooney Bravo( 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. |
Mooney Bravo( structural_deice_type=0 ) Bombardier CRJ 700( structural_deice_type=1 ) |
[piston_engine]
A piston engine's power can be determined through a series of equations that represent the Otto cycle of a four-stroke piston engine, multiplied by the number of pistons available. This section contains all the information needed to be able to determine how much power the engines are capable of producing. Power can also be scaled from the calculated values generated for piston engines with the "power_scalar" property.
Property | Description | Examples |
---|---|---|
detonation_onset | The manifold pressure that if reached or exceeded will lead to the engine detonating. | |
supercharged | On/off. | |
supercharger_boost | Multiplier on manifold pressure if supercharger is engaged.. | |
supercharger_power_cost | Percent of horsepower required to drive supercharger. | |
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. | |
max_rpm_mechanical_efficiency_scalar | Scalar value that can be modified to tune the mechanical efficiency of the engine at maximum rpm. Increase this value to increase the mechanical efficiency, decrease it to decrease the mechanical efficiency. | Mooney Bravo( max_rpm_mechanical_efficiency_scalar= 1.0 ) |
idle_rpm_mechanical_efficiency_scalar | Scalar value that can be modified to tune the mechanical efficiency of the engine at idle rpm. Increase this value to increase the mechanical efficiency, decrease it to decrease the mechanical efficiency. | Mooney Bravo( idle_rpm_mechanical_efficiency_scalar= 1.0 ) |
max_rpm_friction_scalar | Scalar value that can be modified to tune the internal friction of the engine at maximum rpm. Increase this value to increase the friction, decrease it to decrease the friction. |
Mooney Bravo( max_rpm_friction_scalar=1.000 ) |
idle_rpm_friction_scalar | Scalar value that can be modified to tune the internal friction of the engine at idle rpm. Increase this value to increase the friction, decrease it to decrease the friction, (can be used to tune the rpm at which the engine idles). |
Mooney Bravo( idle_rpm_friction_scalar=1.000 ) |
cylinder_displacement | Cubic inches per cylinder displacement. |
Mooney Bravo( cylinder_displacement= 90.3 ) DeHavilland Beaver DHC2( cylinder_displacement= 109.4 ) |
two_stroke_cycle | Two stroke engine. | |
compression_ratio | Compression ratio of each cylinder. |
Mooney Bravo( compression_ratio= 8.0 ) DeHavilland Beaver DHC2( compression_ratio= 6.0 ) |
number_of_cylinders | Integer value; number of cylinders in the engine. |
Mooney Bravo( number_of_cylinders= 6 ) DeHavilland Beaver DHC2( number_of_cylinders=9 ) |
max_rated_rpm | Maximum rated revolutions per minute (RPM) of the engine (red line). |
Mooney Bravo( max_rated_rpm= 2575 ) DeHavilland Beaver DHC2( max_rated_rpm= 2300 ) |
max_rated_hp | Maximum rated brake horsepower output of the engine. |
Mooney Bravo( max_rated_hp= 270 ) DeHavilland Beaver DHC2( 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. |
Mooney Bravo( fuel_metering_type= 0 ) DeHavilland Beaver DHC2( fuel_metering_type = 1 ) |
cooling_type |
Integer value indicating the method of engine cooling, one of: 0 = air cooled 1 = liquid cooled. |
Mooney Bravo( cooling_type= 0 ) |
normalized_starter_torque | This value can be modified to increase/decrease the torque supplied by the starter to get the prop turning. Increase this value for a greater torque effect, decrease it for a lower torque setting. | Mooney Bravo( normalized_starter_torque= 0.3 ) |
turbocharged | Boolean to indicate if the engine is turbocharged; 0 = FALSE, 1 = TRUE. | DeHavilland Beaver DHC2( turbocharged= 1 ) |
max_design_mp | If a turbocharger is present, this value indicates the maximum design manifold pressure supplied by the turbocharger (inHg). |
Mooney Bravo( max_design_mp= 38 ) DeHavilland Beaver DHC2( max_design_mp= 36.5 ) |
min_design_mp | If a turbocharger is present, this value indicates the minimum design manifold pressure of the turbocharger (inHg). |
Mooney Bravo( min_design_mp= 1 ) DeHavilland Beaver DHC2( min_design_mp= 10 ) |
critical_altitude | Altitude to which the turbocharger, if present, will provide the maximum design manifold pressure (feet). |
Mooney Bravo( critical_altitude= 18000 ) DeHavilland Beaver DHC2( critical_altitude= 5000 ) |
emergency_boost_type |
Integer value indicating the emergency boost type available, one of: 0 = None 1 = Water Injection 2 = Methanol/Water Injection 3 = War Emergency Power, (typically used in WWII combat aircraft). |
Mooney Bravo( emergency_boost_type= 0 ) |
emergency_boost_mp_offset | Additional manifold pressure supplied by emergency boost, if available. | Mooney Bravo( emergency_boost_mp_offset= 0.000 ) |
emergency_boost_gain_offset | Multiplier on manifold pressure due to emergency boost. | Mooney Bravo( emergency_boost_gain_offset= 0.000 ) |
fuel_air_auto_mixture | Boolean to indicate if automatic fuel-to-air mixture is available; 0 = FALSE, 1 = TRUE. | Mooney Bravo( fuel_air_auto_mixture= 0 ) |
auto_ignition | Boolean to indicate if automatic ignition is available; 0 = FALSE, 1 = TRUE. | Mooney Bravo( auto_ignition= 0 ) |
power_scalar | Changing this value affects the amount of power delivered by the engine to the propeller shaft. | Mooney Bravo( power_scalar = 1.0 ) |
bestpowerspecificfuelconsumption | Specific fuel consumption at Best Power mixture ratio. | |
magneto_order_left_right_both | Sets the order of the magneto switch direction. | Piper J3 Cub( magneto_order_left_right_both = 1 ) |
number_of_magnetos | Number of magnetos. |
[propeller]
The thrust generated by a given propeller is a function of the power delivered through the propeller shaft, rpm, blade angle, airplane speed, and ambient density.
Property | Description | Examples |
---|---|---|
propeller_type |
Integer that identifies what type of propeller is on the aircraft, one of: 0 = Constant Speed 1 = Fixed Pitch. |
Mooney Bravo( propeller_type= 0 ) |
propeller_diameter | Diameter of propeller blades, tip to tip, in feet. | Mooney Bravo( propeller_diameter= 6.3 ) |
propeller_blades | Integer value indicating the number of blades on the propeller (2, 3 or 4). |
Mooney Bravo( propeller_blades = 4 ) |
propeller_moi | Propeller moment of inertia, (slug ft2). |
Mooney Bravo( propeller_moi= 8.0 ) |
beta_max | Maximum blade pitch angle for constant speed prop (degrees). (Not used if fixed pitch.). |
Mooney Bravo( beta_max = 43 ) DeHavilland Beaver DHC2( beta_max= 24.0 ) |
beta_min | Minimum blade pitch angle for constant speed prop (degrees). (Not used if fixed pitch.). |
Mooney Bravo( beta_min= 15 ) |
min_gov_rpm | The minimum rpm controlled by the governor for a constant speed prop. |
Mooney Bravo( min_gov_rpm= 1100 ) DeHavilland Beaver DHC2( min_gov_rpm= 800 ) |
prop_tc | Time constant for prop. |
Mooney Bravo( prop_tc= 0.1 ) |
gear_reduction_ratio | The reduction ratio from the engine output rpm to prop rpm. |
Mooney Bravo( gear_reduction_ratio= 1.0 ) |
fixed_pitch_beta | Blade pitch angle for fixed pitch prop (degrees). (Not used if constant speed.). |
Mooney Bravo( fixed_pitch_beta= 0 ) |
low_speed_theory_limit | The speed at which low-speed propeller theory gets blended into the high speed propeller theory, (feet/second). |
Mooney Bravo( low_speed_theory_limit= 80 ) |
low_speed_theory_scalar | This scalar can be used to adjust the thrust calculated using the low-speed propeller theory. | low_speed_theory_scalar= 1.8 |
prop_sync_available | Boolean to indicate if propeller-sync is available (twin engine aircraft); 0 = FALSE, 1 = TRUE. | Mooney Bravo( prop_sync_available= 0 ) |
prop_deice_available | Boolean to indicate if propeller de-icing is available; 0 = FALSE, 1 = TRUE. | Mooney Bravo( prop_deice_available= 1 ) |
prop_feathering_available | Boolean to indicate if prop feathering is available (constant speed prop only); 0 = FALSE, 1 = TRUE. | Mooney Bravo( prop_feathering_available= 0 ) |
prop_auto_feathering_available | Boolean to indicate if prop auto-feathering is available (constant speed prop only); 0 = FALSE, 1 = TRUE. | Mooney Bravo( prop_auto_feathering_available= 0 ) |
min_rpm_for_feather | Minimum rpm at which the prop will feather (if feathering is available). | Mooney Bravo( min_rpm_for_feather= 0 ) |
beta_feather | Propeller pitch angle when feathered (degrees). | Mooney Bravo( beta_feather= 0 ) |
power_absorbed_cf | Coefficient of friction power absorbed by propeller. | Mooney Bravo( power_absorbed_cf= 0 ) |
defeathering_accumulators_available | Boolean to indicate if de-feathering accumulators are available; 0 = FALSE, 1 = TRUE. | Mooney Bravo( defeathering_accumulators_available= 0 ) |
prop_reverse_available | Specifies the scalar on the calculated propeller reverser effect. A value of 0 will cause no reverse thrust to be available. A value of 1.0 will cause the theoretical normal thrust to be available. Other values will scale the normal calculated value accordingly. | Mooney Bravo( prop_reverse_available = 0 ) |
minimum_on_ground_beta | Minimum blade pitch angle when the aircraft is on the ground (degrees). | Mooney Bravo( minimum_on_ground_beta= 0 ) |
minimum_reverse_beta | Minimum blade pitch angle when the propeller is in reverse (degrees). |
Mooney Bravo( minimum_reverse_beta= 0 ) |
thrust_scalar | Parameter that scales the calculated thrust provided by the propeller. | Mooney Bravo( thrust_scalar = 1.0 ) |
feathering_switches | Boolean indicating if feathering switches are available. 0 = FALSE, 1 = TRUE. Feathering switches (as found on the Douglas DC3), allow the pilot to automatically feather the propeller via a switch, regardless of the propeller lever position. | |
number_of_propellers | The number of propellers driven per engine. | |
engine_map | Set of flags that allows the propellers to be driven by a different engine. | |
propeller.0 to propeller.1 |
This parameter allows for the propeller to be located at the specified offset (longitudinal, lateral and vertical) in feet from the engine that 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). |
[gpws]
This section specifies the details of the ground proximity warning system.
Property | Description | Examples |
---|---|---|
max_warning_height | The height below which a warning is activated. | |
sink_rate_fpm | If an aircraft exceeds this rate of descent a warning is activated. | |
excessive_sink_rate_fpm | If an aircraft exceeds this rate of descent an urgent warning is activated. | |
climbout_sink_rate_fpm | If an aircraft starts to descend during takeoff, and exceeds this rate of descent, a warning is activated. | |
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. |
[cameraconfiguration]
This section shows the global camera configuration properties that can be set on a per object basis.
Property | Description | Examples |
---|---|---|
CenterOffsetXyz | The global offset of the camera Origin in meters for all camera definitions with Origin type Center. This value will be overridden by the CenterOffsetXyz value of a Camera Definition if present. | CenterOffsetXyz = ( 0.0, 1.5, 0.0 ) |
[cameradefinition.n]
This section shows the camera properties most used by aircraft. An aircraft can have multiple cameradefinition sections, which should be 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 |
DeHavilland Beaver DHC2( title = "Right Float" ) |
guid |
DeHavilland Beaver DHC2( Guid = {B0CA7E72-F3D9-F748-8BF5-108D197B2469} ) |
description |
DeHavilland Beaver DHC2( Description = "View from the aft end of the right float
looking forward" ) |
origin | Mooney Bravo( Origin = Virtual Cockpit ) |
snappbhadjust | DeHavilland Beaver DHC2( SnapPbhAdjust = None ) |
snappbhreturn | |
panpbhadjust | DeHavilland Beaver DHC2( PanPbhAdjust = None ) |
panpbhreturn | |
track | |
showaxis | Mooney Bravo( ShowAxis = FALSE ) |
allowzoom | Mooney Bravo( AllowZoom = TRUE ) |
initialzoom | DeHavilland Beaver DHC2( InitialZoom = .5 ) |
showweather | |
initialxyz |
DeHavilland Beaver DHC2( InitialXyz = 1.5, .5, -3.9 ) |
initialpbh |
DeHavilland Beaver DHC2( InitialPbh = 0, 0, 0 ) |
xyzadjust | |
category | |
momentumeffect | Mooney Bravo( MomentumEffect = TRUE ) |
clipmode | |
zoompanscalar | Mooney Bravo( ZoomPanScalar = 1.0 ) |
showlensflare | Mooney Bravo( ShowLensFlare=FALSE ) |
[turboprop_engine]
The amount of power generated by an engine and the power required for a propeller to turn through the air determine the increase and decrease of the rpm. A turboprop engine is really a combination of a turbine engine and a propeller. The values in this section are included to modify values specific to the turboprop.
Property | Description | Examples |
---|---|---|
power_scalar | Changing this value affects the amount of power delivered by the engine to the propeller shaft. |
Mooney Bravo( power_scalar = 1.0 ) |
maximum_torque | Maximum shaft-torque available from the engine (ft-lbs). | de Havilland Dash 8-100( 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 the airspeed indicators on the instrument panels. The list of indicators should be listed in order: 0,1,2,…n. These characteristics define the calibration between calibrated airspeed and indicated airspeed.
Property | Description | Examples |
---|---|---|
airspeed_indicator.0 to airspeed_indicator.n |
The first parameter is a scalar on the calibrated airspeed, and the second is an offset in knots. The offset is applied first, then the scalar. The default value for the scalar is 1.0 and the default for the offset is 0.0, thus by default indicated airspeed is equal to calibrated airspeed. |
DeHavilland Beaver DHC2( airspeed_indicator.0 = 1, 0 ) Maule M7 260C( airspeed_indicator.0 = 1.3, -24.0 ) |
[pressurization]
This section defines the pressurization characteristics of the aircraft.
Property | Description | Examples |
---|---|---|
design_cabin_pressure | ||
max_pressure_differential |
[variometers]
This section defines the variometers characteristics of the aircraft.
Property | Description | Examples |
---|---|---|
variometer.0 |
[yaw_string]
This section defines the yaw string characteristics of the aircraft.
Property | Description | Examples |
---|---|---|
yaw_string_available |
[water ballast system]
This section defines the water ballast system of the aircraft.
Property | Description | Examples |
---|---|---|
tank.0 | Front Fuselage. | |
tank.1 | Rear Fuselage. | |
tank.2 | Left Outboard. | |
tank.3 | Left Inboard. | |
tank.4 | Right Inboard. | |
tank.5 | Right Outboard. | |
numberofreleasevalves | Number of release valves. | |
dumprate | Gallons per second. |
[smokesystem]
The section describes how to configure a smoke system for an aircraft. You can set multiple smoke points on an aircraft.
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. |
[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 |
|
fold_rates | Two values (for left and right), giving the percentage per second, to fully extend and retract. |
[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. |
[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. | |
rollmomentfromailerons | Scale and offset applied to the roll moment from the ailerons. | |
pitchmomentzeroalpha | Scale and offset applied to the zero angle of attack. |
[antidetonation system.n]
Property | Description | Examples |
---|---|---|
reservoir_size | Gallons. | |
flow_rate | Gallons per minute. | |
reservoir_position | Position relative to datum reference point . | |
max_mp_compensate | Manifold pressure above which AntiDetonation system cannot compensate for. Units are inches of mercury. |
[nitrous system.n]
Property | Description | Examples |
---|---|---|
reservoir_size | Gallons | |
flow_rate | Gallons per minute | |
mp_boost | Multiplier on manifold pressure |
[tailhook]
If a tailhook entry is made, it will override the attachpt_tailhook_pivot and attachpt_tailhook_hook entries for the aircraft, if these attach points exist.
Property | Description | Examples |
---|---|---|
tailhook_length | Length of tailhook in feet. | |
tailhook_position | Tailhook pivot point relative to datum reference point. | |
cable_force_adjust | A scalar value applied to the arrestor cable forces acting upon the aircraft when hooked. | cable_force_adjust = 1.0 |
cable_moment_adjust | A scalar value applied to the arrestor cable moment of force acting upon the aircraft when hooked. | cable_moment_adjust = 0.2 |
[launch_assistance]
If a launch_assistance entry is made, it will override the attachpt_Launch_Bar_Pivot and attachpt_Launch_Bar_Lug entries for the aircraft, if these attach points exist.
Property | Description | Examples |
---|---|---|
launch_bar_pivot | Launch bar pivot point relative to datum reference point. | launch_bar_pivot = 5.0, 0.0, -1.0 |
launch_bar_lug | Launch bar lug point relative to datum reference point. | launch_bar_lug = 5.0, 0.0, -4.5 |
[voicealerts]
Property | Description | Examples |
---|---|---|
lowfuelpct | Three values: Low Fuel limit (percent), check above (1) or below (-1), and check every N seconds. | |
overglimit | High G limit, check above (1) or below (-1), and check every N seconds. |
Helicopter Specific Sections
The following sections are specific to helicopters only. The implementation of the Bell 206 helicopter is a legacy implementation that cannot be configured by changing data in the configuration file. The [helicopter] section is the only helicopter-specific section that is used by the Bell 206. Other helicopter models do use the data in the configuration file to determine their aerodynamic performance, and utilize all the following helicopter-specific 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. | |
low_realism_stability_scale |
This scales the stability of the Bell 206B helicopter to make the aircraft easier
to fly. It has no effect on the other helicopters. The stability factor is broken
down into three components: pitch, bank, and yaw damping. The stability factor is scaled according to the pitch, bank, and yaw values set. For example, increasing the first value (pitch) to 1.1 increases the pitch-damping factor by 10 percent. Increasing these values excessively will result in excessive damping, making it hard to control the helicopter. The stability factor is scaled by the General Flight Model Realism slider in the Realism Settings dialog box. At the highest realism setting, it is scaled to 0% (no additional damping); at the minimum setting, it is scaled to 100 percent. Changes to the stability factor in the .cfg have their largest effect when the Realism Setting is set to minimum, and have no effect when Realism Setting is set to maximum. |
|
reference_length | The length of the helicopter, in feet. | Robinson R22( 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. | Robinson R22( 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. | Robinson R22( 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. | Robinson R22( 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. | Robinson R22( right_trim_scalar = 1.0 ) |
correlator_available | This flag determines if a collective/throttle correlator is configured on the helicopter. | Robinson R22( 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. | Robinson R22( 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 |
Robinson R22( governor_pid = 0.4, 0, 0.1, 0, 0.2 ) |
rotor_brake_scalar | Scalar on the effect of the rotor brake. | Robinson R22( rotor_brake_scalar = 1.0 ) |
torque_scalar | Scalar on the effect that the rotor has on the yawing moment of the helicopter. | Robinson R22( torque_scalar = 1.0 ) |
cyclic_roll_control_scalar | Scalar on the amount of roll control authority from lateral movement of the cyclic. | Robinson R22( 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. | Robinson R22( cyclic_pitch_control_scalar =1.0 ) |
pedal_control_scalar | Scalar on the amount of yaw control authority from movement of the anti-torque pedals. | Robinson R22( 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. | Robinson R22( collective_on_rotor_torque_scalar = 1.0 ) |
[fuselage_aerodynamics]
Property | Description | Examples |
---|---|---|
drag_force_cf | Coefficient of longitudinal drag. | Robinson R22( drag_force_cf = 0.55 ) |
side_drag_force_cf | Coefficient of lateral drag. | Robinson R22( side_drag_force_cf = 10.0 ) |
pitch_damp_cf | Pitch damping coefficient (resistance to pitch velocity). | Robinson R22( pitch_damp_cf = -2.0 ) |
roll_damp_cf | Roll damping coefficient (resistance to roll velocity). | Robinson R22( roll_damp_cf = -2.0 ) |
yaw_damp_cf | Yaw damping coefficient (resistance to yaw velocity). | Robinson R22( yaw_damp_cf = -0.1 ) |
yaw_stability_cf | Yaw stability coefficient. This is the weathervane effect. | Robinson R22( 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_bank_angle | When the stick is centered, the bank angle of the rotor disk, in degrees. | |
position | Position relative to datum reference point. This position should be the center of the main rotor. | Robinson R22( Position = -8.5, 0, 4.91 ) |
radius | The radius of the rotor, in feet. | Robinson R22( Radius = 12.583 ) |
max_disc_angle | The maximum absolute deflection angle up or down, in degrees, that the rotor disc can move with the cyclic. | Robinson R22( max_disc_angle = 5.0 ) |
ratedrpm | The rated rpm value for the main rotor. | Robinson R22( RatedRpm = 510 ) |
number_of_blades | The number of blades in the rotor. | Robinson R22( Number_of_blades = 2 ) |
weight_per_blade | Approximate weight, in pounds, of each rotor blade. | Robinson R22( Weight_per_blade = 26.0 ) |
weight_to_moi_factor | The constant used in calculating the moment of inertia of the rotor disc. The MOI algorithm is a function of the number of blades, their weight, and this constant. Increasing this constant will increase the inertia of the disc. | Robinson R22( Weight_to_moi_factor = 0.58 ) |
inflow_vel_reference | The reference inflow velocity of the air mass moving through the rotor disc. Increasing this value will result in more thrust being generated. | Robinson R22( inflow_vel_reference = 34.0 ) |
[secondaryrotor]
Property | Description | Examples |
---|---|---|
position | Position relative to datum reference point. This position should be the center of the secondary rotor. | Robinson R22( Position = -22.8, -0.74, 1.8 ) |
tailrotor | This flag, if set to 1, configures the secondary rotor as a tail rotor, or anti-torque. | Robinson R22( TailRotor = 1 ) |
radius | The radius of the rotor, in feet. | Robinson R22( Radius = 1.75 ) |
[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_retract_rate | Feet per second. | |
position | Position relative to datum reference point. | |
max_stretch | Max stretch distance at ultimate load. | |
damping_ratio | 0 for no damping to 1.0 for critically damped. | |
rated_load | Characteristics tension of cable in pounds. | |
ultimate_load | Breaking force in pounds. This cannot exceed 10,000lb. | |
tolerance_angle | Angle, in degrees, used to determine lateral breaking force limit. | |
auto_pickup_range | Max Range, in feet, for auto-pickup. | |
auto_pickup_max_speed | Maximum speed (feet per second) for auto-pickup. | |
hoist_payload_station | Payload station in which the hoist will load in and out of. 1 is first station. | |
hoist_door | Door associated with hoist. Must be open for use. |
[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. | |
maximum_torque | Maximum torque available (ft-lbs). | |
powerspecificfuelconsumption | Brake power specific fuel consumption. |