Aircraft Configuration Files
Overview
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
Diamond DA42 aircraft.cfg can be found at
SimObjects\Aircraft\Diamond_DA42\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 are case-sensitive.
See Also
Testing
Changes to the aircraft.cfg file
To see the effects of a change, the flight must be restarted, the quickest way to do this is to .
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 Aircraft Selection Screen; 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 Flight Simulator aircraft model. |
The
visual model (.mdl) file for this aircraft is not compatible with Flight Sim World |
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
New and Changed for Flight Sim WorldThe following sections contain and newly added, changed or removed items for Flight Sim World. They are also included in the main body of the document with a red text highlight.
[fltsim.n]Property | Description | Examples | atc_id_color | This is the colour which will be used to render the tail number. This is a hexadecimal number using ARGB format. | E.g atc_id_color=0xFF0FF00 for pure green. | atc_id_font | This is the font name used for rendering the tail number. The font name must correspond to an entry in Fonts/fonts.json file. | atc_id_font="ARIAL BLACK" | atc_id_render_target_width | This is the width of the render target which will be created to render the tail number. Note that AI aircraft will have this size divided by 2 (e.g. 512) | atc_id_render_target_width=1024 | ui_thumbnailfile | Path to the livery specific image to display as a thumbnail in the UI. 600x240 as PNG or JPEG. | ui_thumbnailfile="texture.1\thumbnail.png" | ui_hangarfile | Path to the livery specific image to display when the livery is selected in the livery selection screen. 1920x1080 as PNG or JPEG. | ui_hangarfile="texture.1\hangar.png" | ui_selectionfile | Path to the livery specific image to display as the background in the hangar when the aircraft is hovered over. 1920x1080 as PNG or JPEG. | ui_selectionfile="texture.1\selection.png" | ui_tilefile | Path to the livery specific image to display on the flight planner tile when the aircraft is selected. 210x44 as PNG or JPEG or the Hangar File can be reused here. | ui_tilefile="texture.1\hangar.png" | ui_visible | If this livery (not aircraft) is visible in the UI. Useful for hiding liveries only used for AI or missions. | ui_visible=TRUE ui_visible=FALSE | description | Removed | | visual_damage | Removed | | prop_anim_ratio | Removed | |
Property | Description | Examples | ai_selection_bias | This should always be 0.0 | ai_selection_bias=0.0 | editable | Removed | | performance | Removed | |
Property | Description | Examples | station_load.0 to station_load.n | Specifies the weight and position of passengers or payload at a station specified with a unique number, station_load.N. Parameters in order are: active, Filled Weight (lbs), Max Weight (lbs),longitudinal, lateral, vertical positions from datum (feet), passenger index. Where long, lat and vertical positions are relative to the datum reference point. The addition of stations results in a corresponding change in aircraft flight dynamics due to the change of the total weight and moments of inertia. Active states if the payload has its filled weight by default before the payload amounts are adjusted. Usually Pilot (potentially also copilot) and some Baggage would be active by default on a GA aircraft. For the passenger index the numbers are as follows: -1 = Not a person (baggage etc) 0 = Pilot 1, 2 ,3 etc = Passengers, matching with those specified in the model.cfg for the aircraft. | station_load.0 = 1, 190, 350, -0.33, -0.90, 1.29, 0 station_load.3 = 0, 170, 350, -3.05, 0.90, 1.21, 3 station_load.5 = 1, 50,100, -4.54, -0.69, 0.42, -1 | station_name.0 to station_name.n | This field is the string name that is used in the Payload dialog (15 character limit). Omission of this will result in a generic station name being used. Note that if passed a translation string e.g @IDS_ST_PILOT only the string ID is limited to 15 characters not the translated result. | station_name.0 = "Payload" station_name.1 = "@IDS_ST_PILOT" station_name.0 = "Pilot" station_name.7 = "Forward Baggage" |
[UI Strings] This section is newly added and contains strings which are used within the User Interface, mostly on the Aircraft Selection screen.
Property | Description | Examples | engine_desc | A short description of the engine of the aircraft. This should fit on one line under the "Engine" heading on the aircraft selection screen. It can be a translation string if required (@IDS_SOMETHING). | engine_desc = "Lycoming IO-360-M1A 180hp @ 2700 rpm" | prop_desc | A short description of the propeller (if applicable) for the aircraft. This should fit on one line under the "Propeller" heading on the aircraft selection screen. It can be a translation string if required (@IDS_SOMETHING). If not applicable for an aircraft use "--". | prop_desc ="MT 3 blade, constant speed" | crew_pass | A string for the amount of crew and passengers the aircraft can have. E.g "1+3, 2+2" for the DA42 which can have 1 crew (pilot) and 3 passengers or 2 crew (pilot+copilot) and 2 passengers. | crew_pass="1+1" | short_desc | A short description of the aircraft to be displayed when the aircraft is selected on the flight planner tile. Should be only a few words, e.g "Innovative, state-of-the-art design" or "Popular two-seat, single-engine monoplane". Can be a translation string (@IDS_SOMETHING) if required. | short_desc="@IDS_SHORT_DESC_RV7A" short_desc="Popular two-seat, single-engine monoplane" |
[Other Reference] This section is newly added and contains reference speeds and distances used in the aircraft specification panel on the aircraft selection screen. Property | Description | Examples | range | Estimated range of the aircraft in nautical miles. This is just for reference on the aircraft selection screen, it will not be used in any flight dynamics calculations. | range = 695 | rate_of_climb | Estimated rate of climb in feet per minute. This is just for reference on the aircraft selection screen, it will not be used in any flight dynamics calculations. | rate_of_climb = 831 | takeoff_distance | Estimated takeoff distance over a 50ft obstacle, in feet. This is just for reference on the aircraft selection screen, it will not be used in any flight dynamics calculations. | takeoff_distance = 1600 | landing_distance | Estimated landing distance over a 50ft obstacle, in feet. This is just for reference on the aircraft selection screen, it will not be used in any flight dynamics calculations. | landing_distance = 1525 | ceiling | Estimated service ceiling of the aircraft, in feet. This is just for reference on the aircraft selection screen, it will not be used in any flight dynamics calculations. | ceiling = 18000 | fuel_capacity | Reference fuel capacity of the aircraft, in US gallons. This is just for reference on the aircraft selection screen, it will not be used in any flight dynamics calculations. | fuel_capacity = 79.4 | fuel_consumption_at_cruise | Estimated fuel consumption at cruise of the aircraft, in US Gallons Per Hour. This is just for reference on the aircraft selection screen and for calculating estimated endurance to be displayed on the pause screen, it will not be used in any flight dynamics calculations. | fuel_consumption_at_cruise = 13 |
[Accufeel] This section is newly added and contains parameters to adjust the impact of Accu-Feel™ on the aircraft. It allows each aircraft to be tuned with custom parameters for Accu-Feel™. Property | Description | Examples | AccufeelOn | Master on/off for Accu-Feel™ on the aircraft. | AccuFeelOn = 1 | MasterVolume | Master volume of Accu-Feel™ for this aircraft. | MasterVolume = 75 | GlobalTurbulenceStrength | | GlobalTurbulenceStrength = 50 | GlobalTurbulenceVolume | | GlobalTurbulenceVolume = 50 | OpenCockpit | If the aircraft has an open cockpit. | OpenCockpit = 0 | AircraftVolume | | AircraftVolume = 75 | StallAoA | | StallAoA = 16 | Stall_Instability | | Stall_Instability = 40 | MaxMach | Max mach (Vne) of the aircraft. | MaxMach = 0.281 | MaxIAS | Max IAS (Vne) of the aircraft. | MaxIAS = 188 | WindVolume | | WindVolume = 40 | PropVolume | | PropVolume = 50 | DragRumble | | DragRumble = 35 | Chop | | Chop = 30 | Gusts | | Gusts = 40 | ClearAirTurbulence | | ClearAirTurbulence = 40 | CabinIntegrity | | CabinIntegrity = 85 | ShockAbsorption | | ShockAbsorption = 80 | BrakeSqueal | | BrakeSqueal = 12 | TireScreech | | TireScreech = 60 | TireSideForces | | TireSideForces = 35 | WaterDrag | | WaterDrag = 50 | AutoWaves | | AutoWaves = 1 | WaveSize | | WaveSize = 25 | WaveSpeed | | WaveSpeed = 50 |
The model.cfg section at the end of this document has been updated for Flight Sim World and should be read in full.
Additional Sections
[antidetonation system.n]
Property
|
Description
|
Examples
|
reservoir_size |
Gallons. |
reservoir_size = 4 |
flow_rate |
Gallons per minute. |
flow_rate = 3. |
reservoir_position |
Position relative to datum reference point . |
reservoir_position = -1.8, 4.1, -1.8 |
max_mp_compensate |
Manifold pressure above which AntiDetonation system cannot compensate for. Units are inches of mercury. |
max_mp_compensate = 135 |
[nitrous system.n]
Property
|
Description
|
Examples
|
reservoir_size |
Gallons |
reservoir_size=10.0 |
flow_rate |
Gallons per minute |
flow_rate=5.0 |
mp_boost |
Multiplier on manifold pressure |
mp_boost=1.75 |
[tailhook]
Property
|
Description
|
Examples
|
tailhook_length |
Length of tailhook in feet. |
tailhook_length = 4.5 |
tailhook_position |
Tailhook pivot point relative to datum reference point . |
tailhook_position = -49.0, 0, -2.5 |
[voicealerts]
Property
|
Description
|
Examples
|
lowfuelpct |
Three values: Low Fuel limit (percent), check above (1) or below (-1), and check every N seconds. |
LowFuelPct = 0.1, -1, 60 |
overglimit |
High G limit, check above (1) or below (-1), and check every N seconds. |
OverGLimit = 6.0, 1, 1 ) |
Standard Sections
[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 Diamond DA42,
all
housed in the same DA42 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=g1000 means that
this version of the DA42 uses the panel files in the panel.g1000 subfolder.
When creating and referencing multiple model, panel, sound,
and texture directories, use the naming convention
foldername.extension,
where the extension is a unique identifier for
that configuration set (for example, .g1000). To refer to the folder from
the
relevant parameter in the aircraft.cfg file, just specify the extension
(for example, panel=g1000).
If a parameter is not explicitly set it automatically refers
to
the default (extension-less) folder.
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 DA42 configurations use the same sounds, and thus the
sound parameters in all the fltsim sections point to the
single sound
folder in the DA42 folder.
Each aircraft defined by a configuration set will appear as a
separate listing in the Aircraft livery screen. 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. |
Diamond DA42 ( title=Diamond DA42 Twin Star )
Piper PA28( title=Piper PA-28 Cherokee 180 )
|
sim |
Specifies which .air (flight model) file (located in
the aircraft folder) to use. |
Diamond DA42 ( sim=DA42 )
Piper PA28 ( sim=Piper_PA28_180) |
model |
Specifies which model folder to reference. If no entry
is made, the default folder is used. |
Diamond DA42 ( model= ) |
panel |
Specifies which panel folder to reference. |
Diamond DA42 ( panel= ) |
sound |
Specifies which sound folder to reference. |
Diamond DA42 ( sound= ) |
texture |
Specifies which texture folder to reference. |
Diamond DA42 ( texture=2)
Piper PA28 ( texture= ) |
kb_checklists |
Deprecated, leave blank. |
kb_checklists= |
kb_reference |
Deprecated, leave blank. |
kb_reference= |
atc_id |
The tail number displayed on the exterior of the
aircraft. Note that
custom tail numbers burned into textures will not be modified by
this. |
Diamond DA42( atc_id="N42DA" ) |
atc_id_color |
This is the colour which will be used to render the tail number. This is a hexadecimal number using ARGB format. |
E.g atc_id_color=0xFF0FF00 for pure green. |
atc_id_font |
This is the font name used for rendering the tail number. The font name must correspond to an entry in Fonts/fonts.json file. |
atc_id_font="ARIAL BLACK" |
atc_id_render_target_width |
This is the width of the render target which will be created to render the tail number. Note that AI aircraft will have this size divided by 2 (e.g. 512) |
atc_id_render_target_width=1024 |
atc_airline |
The ATC system will use the specified airline name with
this aircraft. This is dependant on ATC recognizing the name. ATC will
treat this aircraft as an airliner when this is used in conjunction
with atc_flight_number. |
atc_airline="Airline Name" |
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. |
atc_flight_number=1123 |
ui_manufacturer |
This value identifies the manufacturer sub-category
used to group aircraft in the select aircraft dialog inside Flight Sim World. |
ui_manufacturer="Diamond"
ui_manufacturer="Piper" |
ui_type |
This value identifies the type sub-category used to
group aircraft in the select aircraft dialog inside Flight Sim World. |
ui_type=DA42 Twin Star |
ui_variation |
This value identifies the variation sub-category used
to group aircraft in the select aircraft dialog inside Flight Sim World. |
ui_variation="@IDS_AIRCRAFT_LIVERY_TYPE_STRIPE_2" |
ui_typerole |
This value identifies the role of the aircraft. |
ui_typerole="@IDS_TYPE_TWIN_PROP"
ui_typerole="Commercial Airliner" |
ui_createdby |
This value is used to identify the creator of the
configuration file. |
ui_createdby="Dovetail Games" |
ui_thumbnailfile |
Path to the livery specific image to display as a thumbnail in the UI. 600x240 as PNG or JPEG. |
ui_thumbnailfile="texture.1\thumbnail.png" |
ui_hangarfile |
Path to the livery specific image to display when the livery is selected in the livery selection screen. 1920x1080 as PNG or JPEG. |
ui_hangarfile="texture.1\hangar.png" |
ui_selectionfile |
Path to the livery specific image to display as the background in the hangar when the aircraft is hovered over. 1920x1080 as PNG or JPEG. |
ui_selectionfile="texture.1\selection.png" |
ui_tilefile |
Path to the livery specific image to display on the flight planner tile when the aircraft is selected. 210x44 as PNG or JPEG or the Hangar File can be reused here. |
ui_tilefile="texture.1\hangar.png" |
ui_visible |
If this livery (not aircraft) is visible in the UI. Useful for hiding liveries only used for AI or missions. |
ui_visible=TRUE
ui_visible=FALSE |
atc_heavy |
Setting this flag to 1 will result in the ATC system
appending the phrase heavy to the aircrafts callsign. |
atc_heavy=0
atc_heavy=1 |
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. |
atc_parking_types=RAMP
atc_parking_types=CARGO
atc_parking_types=GATE,RAMP |
atc_parking_codes |
Specifies one or more ICAO airline designations so that ATC can direct the aircraft to a gate that has also been designated specifically for that same airline, for example, "DTA" for Dovetail Airlines. |
Refer to the example XML for the TaxiwayParking entry in the Compiling BGL document. The codes entered in the airlineCodes entry should match the text entered here. The ICAO codes do not have to be used, and can be as short as one character, as long as the text strings match, but for clarity use of the ICAO codes is recommended.
If mutliple parking codes are entered, separate them with commas.
|
[general]
In addition to the fltsim sections, the general
section
contains information related to all variations of the aircraft. For
example, the Cessna 182RG, 182S, and 182S IFR are all the same type of
aircraft, and contain the same flight model. As such,
there are some things that are not variable
across variations:
Property
|
Description
|
Examples
|
atc_type |
This is the specific aircraft type that the ATC system
recognizes for this type of aircraft. |
atc_type=Piper
atc_type=Diamond |
atc_model |
This is the specific aircraft model that the ATC system
recognizes for this type of aircraft. Note: atc_type + atc_model when combined should be unique to an aircraft. |
atc_model=PA28
atc_model=DA42
atc_model=P28R |
category |
For aircraft, one of airplane or helicopter. |
Category = airplane
Category = Helicopter |
ai_selection_bias |
This should always be 0.0 |
ai_selection_bias=0.0 |
[pitot_static]
The vertical_speed_time_constant parameter can be used to 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. |
vertical_speed_time_constant = 1
vertical_speed_time_constant = 1.0
vertical_speed_time_constant = 4 |
pitot_heat |
Scale of heat effectiveness, or 0 if not available. |
pitot_heat = 1.0
pitot_heat=0.000000
pitot_heat = 0. |
[weight_and_balance]
The weight and center of gravity of the aircraft can 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. |
max_gross_weight = 150000
max_gross_weight= 600.000
max_gross_weight = 875000
max_gross_weight = 5524 |
empty_weight |
Total weight (in pounds) of the aircraft minus usable
fuel, passengers, and cargo. If not specified, the value previously set
in the
.air file will be used. |
empty_weight = 74170
empty_weight= 310.000
empty_weight = 394088
empty_weight = 3911 |
reference_datum_position |
Offset (in feet) of the aircraft's reference datum from
the standard Flight Sim World center point, which is on the centerline
chord aft of the leading edge. By setting the Reference Datum Position,
actual aircraft loading data can be used directly according to the
aircraft's manufacturer. If not specified, the default is 0,0,0. |
reference_datum_position=
0.000, 0.000,
0.000
reference_datum_position = 83.5, 0, 0
reference_datum_position = 6.96, 0, 0 |
empty_weight_cg_position |
Offset (in feet) of the center of gravity of the basic
empty aircraft (no fuel, passengers, or baggage) from the datum reference point . |
empty_weight_CG_position=
0.000, 0.000,
0.000
empty_weight_CG_position = -90.5, 0, 0
empty_weight_CG_position = -6.06, 0, 0 |
max_number_of_stations |
Specifies the maximum number of
stations Flight Sim World will calculate when the aircraft is loaded.
This allows an unlimited number of stations to be specified. Note that
an excessively large number here results in a longer load time for the
aircraft when selected, although there is no effect on real-time
performance. |
max_number_of_stations = 50 |
station_load.0
to
station_load.n |
Specifies the weight and position of passengers or
payload at a station specified with a unique number, station_load.N. Parameters in order are: active, Filled Weight (lbs), Max Weight (lbs),longitudinal, lateral, vertical positions from datum (feet), passenger index. Where long, lat and vertical positions are relative to the datum reference point. The addition
of stations results in a corresponding change in aircraft flight
dynamics due to the change of the total weight and moments of inertia. Active states if the payload has its filled weight by default before the payload amounts are adjusted. Usually Pilot (potentially also copilot) and some Baggage would be active by default on a GA aircraft.
For the passenger index the numbers are as follows:
-1 = Not a person (baggage etc)
0 = Pilot
1, 2 ,3 etc = Passengers, matching with those specified in the model.cfg for the aircraft. |
station_load.0 = 1, 190, 350, -0.33, -0.90, 1.29, 0
station_load.3 = 0, 170, 350, -3.05, 0.90, 1.21, 3
station_load.5 = 1, 50,100, -4.54, -0.69, 0.42, -1 |
station_name.0
to
station_name.n |
This field is the string name that is used in the
Payload dialog (15 character limit). Omission of this will result in a
generic station name being used. Note that if passed a translation string e.g @IDS_ST_PILOT only the string ID is limited to 15 characters not the translated result.
|
station_name.0
= "Payload"
station_name.1 = "@IDS_ST_PILOT"
station_name.0 = "Pilot"
station_name.7 = "Forward
Baggage" |
empty_weight_pitch_moi |
The moment of inertia (MOI) about the lateral axis. |
empty_weight_pitch_MOI = 3172439
empty_weight_pitch_MOI= 230.000
empty_weight_pitch_MOI = 24223159
empty_weight_pitch_MOI = 3905.65 |
empty_weight_roll_moi |
The moment of inertia (MOI) about the longitudinal
axis. |
empty_weight_roll_MOI = 2262183
empty_weight_roll_MOI= 205.000
empty_weight_roll_MOI = 13352310
empty_weight_roll_MOI = 2718.64 |
empty_weight_yaw_moi |
The moment of inertia (MOI) about the vertical axis. |
empty_weight_yaw_MOI = 3337024
empty_weight_yaw_MOI= 290.000
empty_weight_yaw_MOI = 39531785
empty_weight_yaw_MOI = 5291.04 |
empty_weight_coupled_moi |
The moment of inertia (MOI) about the roll and yaw axis
(usually zero). |
empty_weight_coupled_MOI = 0
empty_weight_coupled_MOI= 0.000
empty_weight_coupled_MOI= 0.0
empty_weight_coupled_MOI = 0.0 |
[flight_tuning]
Flight control effectiveness parameters
The elevator, aileron and elevator effectiveness 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. |
cruise_lift_scalar = 1.0
cruise_lift_scalar=1.000 |
parasite_drag_scalar |
Cd0. |
parasite_drag_scalar = 1.0
parasite_drag_scalar=1.000 |
induced_drag_scalar |
Cdi. |
induced_drag_scalar = 1.0
induced_drag_scalar=1.000 |
elevator_effectiveness |
Cmde. |
elevator_effectiveness = 1.0
elevator_effectiveness=1.000 |
aileron_effectiveness |
Clda. |
aileron_effectiveness = 1.0
aileron_effectiveness=1.000 |
rudder_effectiveness |
Cndr. |
rudder_effectiveness = 1.0
rudder_effectiveness=0.501 |
pitch_stability |
Cmq. |
pitch_stability = 1.0
pitch_stability=1.000 |
roll_stability |
Clp. |
roll_stability = 1.0
roll_stability=1.000 |
yaw_stability |
Cnr. |
yaw_stability = 1.0
yaw_stability=1.000 |
elevator_trim_effectiveness |
Cmdetr. |
elevator_trim_effectiveness = 1.0
elevator_trim_effectiveness=1.000 |
aileron_trim_effectiveness |
Cldatr. |
aileron_trim_effectiveness = 1.0
aileron_trim_effectiveness=1.000 |
rudder_trim_effectiveness |
Cndrtr. |
rudder_trim_effectiveness = 1.0
rudder_trim_effectiveness=1.000 |
hi_alpha_on_roll |
See notes above. |
|
hi_alpha_on_yaw |
|
|
p_factor_on_yaw |
See notes above. |
p_factor_on_yaw = 0.5
p_factor_on_yaw = 0.3 |
torque_on_roll |
|
torque_on_roll = 1.0
torque_on_roll = 0.5
torque_on_roll = 0.3 |
gyro_precession_on_yaw |
See notes above. |
gyro_precession_on_yaw = 1.0
gyro_precession_on_yaw = 0.3 |
gyro_precession_on_pitch |
|
gyro_precession_on_pitch = 1.0
gyro_precession_on_pitch = 0.3 |
[generalenginedata]
Every type of aircraft, even a glider, should have 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. |
engine_type = 1
engine_type= 0
engine_type = 0
engine_type = 5 |
engine.0
to
engine.n |
Offset of the engine from the datum reference point. Each engine location
specified increases the engine count (maximum of four engines allowed). |
Engine.0 = 4.75, -16.1, -4.5
Engine.0= -3.000, 0.000, 2.000
Engine.0 = -1.4, -5.3, 0.0
Engine.0 = -107.5, -69.5, -6.9
Engine.1 = -76.0, -38.9, -10.4
Engine.2 = -76.0, 38.9, -10.4
Engine.3 = -107.5, 69.5, -6.9
|
fuel_flow_scalar |
Scalar for modifying the fuel flow required by 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. |
fuel_flow_scalar = 1
fuel_flow_scalar= 1.000
fuel_flow_scalar = 1.0
fuel_flow_scalar= 0.9 |
min_throttle_limit |
Defines the minimum throttle position (percent of max).
Normally 0 for piston aircraft and -0.25 for turbine airplane engines
with reverse thrust. |
min_throttle_limit = -0.25
min_throttle_limit=0.000000
min_throttle_limit = -0.25;
min_throttle_limit = 0.0; |
max_contrail_temperature |
Ambient temperature, in celsius, in which engine 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. |
max_contrail_temperature = -30 |
master_ignition_switch |
1=Available, 0=Not Available (default). If available,
this switch must be on for the ignition circuit, and thus the engines,
to be operable. Turning it off will stop all engines. |
master_ignition_switch = 1 |
starter_type |
Set
to 1 for a Manual Starter |
starter_type = 1 |
thrustanglepitchheading.0 |
Thrust pitch and heading angles in degrees ( positive pitch down, positive heading right). |
ThrustAnglePitchHeading.0 = 0,0 |
[turbineenginedata]
A turbine engine ignites fuel and compressed air to 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. |
fuel_flow_gain = 0.002
fuel_flow_gain = 0.002
fuel_flow_gain = 0.011
fuel_flow_gain = 0.0025 |
inlet_area |
Engine nacelle inlet area, (in square feet). |
inlet_area = 19.6
inlet_area = 60.0
inlet_area = 1.0
inlet_area = 9.4 |
rated_n2_rpm |
Second stage compressor rated rpm. |
rated_N2_rpm = 29920
rated_N2_rpm = 29920
rated_N2_rpm = 33000 |
static_thrust |
Maximum rated static thrust at sea level (lbs). |
static_thrust = 23500
static_thrust = 56750
static_thrust = 158
static_thrust = 12670 |
afterburner_available
afterburner_available
|
Boolean value to indicate if an afterburner is
available; 0 = FALSE, 1 = TRUE.
This has been extended to take a number, indicating the number of afterburner stages available.
|
afterburner_available = 0
afterburner_available = 6
|
reverser_available |
Specifies the scalar on the calculated reverse thrust
effect. A value of 0 will cause no reverse thrust to be available. A
value of 1.0 will cause the theoretical normal reverse thrust to be
available. Other values will scale the normal calculated value
accordingly. |
reverser_available = 1
reverser_available = 0 |
thrustspecificfuelconsumption |
Jet thrust specific fuel consumption. The ratio of fuel used in pounds per hour, to thrust in pounds. Applies at all speeds. |
ThrustSpecificFuelConsumption = 0.6
ThrustSpecificFuelConsumption = 0.4 |
afterburnthrustspecificfuelconsumption |
Jet thrust specific fuel consumption. The ratio of fuel used in pounds per hour, to thrust in pounds. Applies only when the afterburner is active. |
AfterBurnThrustSpecificFuelConsumption = 0
AfterBurnThrustSpecificFuelConsumption = 0.5
|
afterburner_throttle_threshold |
Percentage of throttle range when the afterburner engages. |
afterburner_throttle_threshold = 0.76 |
[jet_engine]
The thrust_scalar parameter scales the calculated thrust for jet
engines (thrust taken from the
[TurbineEngineData] section).
Property
|
Description
|
Examples
|
thrust_scalar |
Parameter that scales the calculated thrust provided by
the propeller. |
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 |
flap_motor = 0, 5 , 17.0 |
gear_motor |
Bus type, max amp, min voltage |
gear_motor = 0, 5 , 17.0 |
autopilot |
Bus type, max amp, min voltage |
autopilot = 0, 5 , 17.0 |
avionics_bus |
Bus type, max amp, min voltage |
avionics_bus = 0, 5, 17.0
avionics_bus = 0, 5 , 17.0
avionics_bus = 0, 5 , 9.5 |
avionics |
Bus type, max amp, min voltage |
avionics = 1, 5 , 17.0
avionics = 1, 5 , 9.5 |
pitot_heat |
Bus type, max amp, min voltage |
pitot_heat = 0, 2 , 17.0 |
additional_system |
Bus type, max amp, min voltage |
additional_system = 0, 2, 17.0
additional_system = 0, 2 , 17.0
additional_system = 0, 2 , 9.5 |
marker_beacon |
Bus type, max amp, min voltage |
marker_beacon = 1, 2 , 17.0
marker_beacon = 1, 2 , 9.0 |
gear_warning |
Bus type, max amp, min voltage |
gear_warning = 0, 2 , 17.0 |
fuel_pump |
Bus type, max amp, min voltage |
fuel_pump = 0, 5 , 17.0
fuel_pump = 0, 5 , 9.0 |
starter1 |
Bus type, max amp, min voltage |
starter1 = 0, 20, 17.0 |
starter2 |
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 |
light_nav = 0, 5 , 17.0 |
light_beacon |
Bus type, max amp, min voltage |
light_beacon = 0, 5 , 17.0 |
light_landing |
Bus type, max amp, min voltage |
light_landing = 0, 5 , 17.0 |
light_taxi |
Bus type, max amp, min voltage |
light_taxi = 0, 5 , 17.0 |
light_strobe |
Bus type, max amp, min voltage |
light_strobe = 0, 5 , 17.0 |
light_panel |
Bus type, max amp, min voltage |
light_panel = 0, 5 , 17.0 |
light_cabin |
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. |
max_battery_voltage = 24.0
max_battery_voltage = 24
max_battery_voltage = 12.0 |
generator_alternator_voltage |
Voltage of the generators or alternators. |
generator_alternator_voltage
= 28.0
generator_alternator_voltage = 25.0
generator_alternator_voltage = 28
generator_alternator_voltage = 25 |
max_generator_alternator_amps |
Maximum generator/alternator amps. |
max_generator_alternator_amps
= 60.0
max_generator_alternator_amps = 40.0
max_generator_alternator_amps = 50
max_generator_alternator_amps = 100 |
engine_generator_map |
List
of flags, corresponding to the number of engines, indicating whether
there is a generator configured with the engine. |
engine_generator_map= 0,1,0
|
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 osciallation. 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. |
point.0=1, 40.00, 0.00, -8.40,
1181.1, 0, 1.442, 55.92, 0.6, 2.5, 0.9, 4.0, 4.0, 0, 220.0, 250.0
point.0= 1.000, 2.583, 0.000, -1.000,
1574.803, 0.000, 0.504, 31.860, 0.235, 2.500, 0.731, 0.000, 0.000,
0.000, 0.000, 0.000
point.0 = 1, 0.82, 0.00, -3.77, 1600, 0,
0.633, 40, 0.42, 4.0, 0.90, 3.0, 3.0, 0, 152, 180
point.0 = 1, -25.0, 0.0, -17.5, 1000.0, 0,
2.0, 70.0, 0.5, 3.5, 0.900, 9.0, 8.0, 0, 220, 250
point.1 = 1, -114.0, -18.0, -21.3, 2000.0, 1,
2.0, 13.0, 3.0, 2.5, 0.900, 11.0, 9.0, 2, 220, 250
point.2 = 1, -114.0, 18.0, -21.3, 2000.0, 2,
2.0, 13.0, 3.0, 2.5, 0.900, 11.0, 9.0, 3, 220, 250
point.3 = 2, -152.6, -103.5, 3.0, 700.0, 0,
0.0, 0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 5, 0, 0
point.4 = 2, -152.6, 103.5, 3.0, 700.0, 0,
0.0, 0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 6, 0, 0
point.5 = 2, 3.0, 0.0, 0.0, 700.0, 0, 0.0,
0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 9, 0, 0
point.6 = 2, -222.7, 0.0, 4.0, 700.0, 0, 0.0,
0.0, 0.0, 0.0, 0.000, 0.0, 0.0, 4, 0, 0
|
max_number_of_points |
Integer value indicating the maximum number of contact
points
the program will look for. |
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. |
static_pitch=0.04
static_pitch= 0.000
static_pitch = -1.5
static_pitch = 1.56 |
static_cg_height |
The static height of the aircraft when at rest on 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. |
static_cg_height=7.67
static_cg_height= 1.000
static_cg_height = 18.6
static_cg_height = 3.43 |
gear_system_type |
This parameter defines the system type which drives the
gear extension and retraction.
0 = electrical
1 = hydraulic
2 = pneumatic
3 = manual
4 = none |
gear_system_type=1
gear_system_type=0
gear_system_type=3 |
emergency_extension_type |
One of:
None=0,Pump=1,Gravity=2. |
emergency_extension_type=2 |
tailwheel_lock |
Boolean defining if a tailwheel lock is available
(applicable only on tailwheel airplanes). |
tailwheel_lock = 1 |
[gear_warning_system]
The following parameters define the functionality of 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). |
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). |
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. |
flap_limit_idle = 5.0
flap_limit_idle = 0.0
flap_limit_idle = 15.0 |
flap_limit_power |
The flap limit, above which the warning will activate
(regardless of throttle position). |
flap_limit_power = 25.5
flap_limit_power = 31.5 flap_limit_power = 30.0 flap_limit_power = 16.0 |
[brakes]
The following parameters define the aircraft's braking system:
Property
|
Description
|
Examples
|
parking_brake |
Boolean setting if a parking brake is available on the
aircraft. |
parking_brake = 1
parking_brake=1
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. |
toe_brakes_scale = 0.885
toe_brakes_scale=1.000031
toe_brakes_scale = 1.24
toe_brakes_scale = 1.0 |
auto_brakes |
The number of increments that the auto-braking switch can be turned to. |
auto_brakes = 3
auto_brakes = 4
auto_brakes = 0 |
hydraulic_system_scalar |
The ratio of hydraulic system pressure to maximum brake
hydraulic pressure. |
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. |
differential_braking_scale = 1.0 |
[hydraulic_system]
The following parameters define the aircraft's hydraulic system:
Property
|
Description
|
Examples
|
normal_pressure |
The normal operating pressure of the hydraulic system,
in pounds per square inch. |
normal_pressure = 3000.0
normal_pressure=0.000000
normal_pressure = 0.0
normal_pressure = 1000.0 |
electric_pumps |
The number of electric hydraulic pumps the aircraft is
configured with. |
electric_pumps = 0
electric_pumps = 1 |
engine_map |
This series of flags sets whether the corresponding
engines of the aircraft are configured with hydraulic pumps. The flags
correspond in order of the engines, starting with the left-most engine
first and moving right. By default, all engines are equipped to drive a
hydraulic pump. |
engine_map = 1,1,0,0
engine_map = 1,1,1,1
engine_map = 1,0,0,0
engine_map = 1 |
[views]
The following parameter define the pilot's viewpoint.
Property
|
Description
|
Examples
|
eyepoint |
Position relative to datum reference point. |
eyepoint=48.2, -1.35, 1.7
eyepoint=-0.205052,0.000000,3.604314
eyepoint = -18.55, -1.97, 10.7
eyepoint = -8.213, -0.8612, 2.220 |
zoom |
Zoom
the view in or out from the viewpoint. |
zoom=1.0 |
[flaps.n]
For each flap set that is on the aircraft, a corresponding [flaps.n] section should exist. Most general aviation aircraft and
smaller jets only have one set of flaps (trailing edge), but it is
typical for the larger commercial aircraft to have a set of leading
edge flaps in addition to the trailing edge flaps. The number
of flap sets are determined by the number of [flaps.n] 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. |
type = 1
type=0
type = 2
type=1 |
span-outboard |
The percentage of half-wing span the flap extends to
(from the wing-fuselage intersection). |
span-outboard = 0.8
span-outboard=0.500000
span-outboard = 0.41
span-outboard = 0.5 |
extending-time |
Time it takes for the flap set to extend to the fullest
deflection angle specified (seconds). |
extending-time = 20
extending-time=0.000000
extending-time = 2
extending-time = 25 |
flaps-position.0
to
flaps-position.n |
Each element of the flaps-position array indicates the
deflection angle to which the flaps will deflect (in degrees). The
largest
deflection angle will be the one used for full flap deflection. |
flaps-position.0= 0
flaps-position.0 = -9.0
flaps-position.0 = -7
flaps-position.0 = 0
flaps-position.1 = 1
flaps-position.2 = 2
flaps-position.3 = 5
flaps-position.4 = 10
flaps-position.5 = 15
flaps-position.6 = 25
flaps-position.7 = 30
flaps-position.8 = 40 |
damaging-speed |
Speed at which the flaps begin to accrue damage (Knots
Indicated Airspeed, KIAS). |
damaging-speed = 250
damaging-speed = 200
damaging-speed = 152
damaging-speed = 120 |
blowout-speed |
Speed at which the flaps depart the aircraft (Knots
Indicated Airspeed, KIAS). |
blowout-speed = 300
blowout-speed = 250
blowout-speed = 150
blowout-speed = 175 |
lift_scalar |
The percentage of total lift due to flap deflection
that this flap set is responsible for at full deflection. |
lift_scalar = 1.0
lift_scalar = 0.7 |
drag_scalar |
The percentage of total drag due to flap deflection
that this flap set is responsible for at full deflection. |
drag_scalar = 1.0
drag_scalar = 0.9 |
pitch_scalar |
The percentage of total pitch due to flap deflection
that this flap set is responsible for at full deflection. |
pitch_scalar= 1.0
pitch_scalar= 0.9 |
system_type |
Integer value that indicates what type of system drives
the flaps to deflect:, one of:
0 = Electric
1 = Hydraulic
2 = Pneumatic
3 = Manual
4 = None |
system_type = 1
system_type=0
system_type = 0
system_type = 3 |
[radios]
There should be a radio section in 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. |
Audio.1 = 1
Audio.1 = 0 |
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. |
Com.1 = 1, 1
Com.1 = 1, 0 |
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. |
Com.2 = 1, 1
Com.2 = 1, 0 |
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. |
Nav.1 = 1, 1, 1
Nav.1 = 1, 0, 1
Nav.1 = 0, 0, 0 |
nav.2 |
Three flags, set the first to 1 if there is 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. |
Nav.2 = 1, 1, 0
Nav.2 = 1, 0, 0 |
adf.1 |
If there is an ADF receiver, set to 1. |
Adf.1 = 1
Adf.1 = 0 |
adf.2 |
If
there is an ADF2 receiver, set to 1. |
Adf.2 = 1 |
transponder.1 |
If there is a transponder, set to 1. |
Transponder.1 = 1
Transponder.1 = 0 |
marker.1 |
If there is a marker beacon receiver, set to 1. |
Marker.1 = 1
Marker.1 = 0 |
[lights]
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 |
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 Flight Sim World/effects folder. |
light.0 = 3, -19.14, -47.24,
1.38, fx_navredm ,
light.0 = 3, -150.30, -102.56, 3.22,
fx_navredh ,
light.0 = 3, -6.60, -19.29, 0.79, fx_navred ,
light.0 = 3, 0.56, -28.41, 1.97,
fx_navred ,
light.1 = 3, 0.56, 28.41, 1.97, fx_navgre
,
light.2 = 3, -31.20, 0.00, 9.09,
fx_navwhi ,
light.3 = 2, 0.89, -28.48, 1.87,
fx_strobe , |
[keyboard_response]
The aircraft flight controls can be manipulated by 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. |
elevator = 150, 250
elevator=150.000000,250.000000
elevator = 100, 180
elevator = 160, 360 |
aileron |
Two breakpoint speeds for keypress increments. |
aileron = 150, 250
aileron=150.000000,250.000000
aileron = 200, 1000
aileron = 160, 360 |
rudder |
Two breakpoint speeds for keypress increments. |
rudder = 150, 250
rudder=150.000000,250.000000
rudder = 200, 1000
rudder = 160, 360 |
[direction_indicators]
This section is used to define the characteristics of the 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 |
direction_indicator.0=3,0
direction_indicator.0 = 0
direction_indicator.0=1,0
direction_indicator.0=0,0
direction_indicator.1=2,0 |
induction_compass.0
to
induction_compass.n |
If
there is an induction compass, one of:
1 = Electric
2 = Anemometer driven |
induction_compass.0=2 |
[attitude_indicators]
This section is used to define the characteristics of the attitude
indicators on the instrument panels. The list of indicators should 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 |
attitude_indicator.0 = 2
attitude_indicator.0=1
attitude_indicator.0 = 1
attitude_indicator.0 = 0
attitude_indicator.1 = 1
attitude_indicator.1 = 2 |
[altimeters]
Property
|
Description
|
Examples
|
altimeter.0
to
altimeter.n
|
If the parameter is set to 1, a separate altimeter is instantiated, which will operate independently of other altimeters, and can have failures applied to it. |
altimeter.0=1
altimeter.0 = 1
altimeter.1=1
altimeter.1 = 1
|
[turn_indicators]
This section is used to define the characteristics of the 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 dependant. The first value is for turn,
the second for bank. The codes are:
0 = None
1 = Electrically driven gyro
2 = Vacuum driven gyro |
turn_indicator.0=0,0
turn_indicator.0=1,0
turn_indicator.0=1,1
turn_indicator.0=1 |
[vacuum_system]
The following parameters define the aircraft's vacuum system:
Property
|
Description
|
Examples
|
max_pressure |
Maximum pressure in psi. |
max_pressure=5.15
max_pressure=5.000000
max_pressure=5.150000
max_pressure=0 |
vacuum_type |
Vacuum type, one of:
0 = None
1 = Engine pump (default)
2 = Pneumatic
3 = Venturi. |
vacuum_type=2
vacuum_type=1
vacuum_type=0 |
electric_backup_pressure |
Backup pressure in psi. |
electric_backup_pressure=0.000000
electric_backup_pressure=4.900000
electric_backup_pressure=4.9
electric_backup_pressure=5.15 |
engine_map |
This series of flags sets whether the 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. |
engine_map=1,1
engine_map=1 |
[pneumatic_system]
The following parameters define the aircraft's pneumatic pressure
system:
Property
|
Description
|
Examples
|
max_pressure |
The maximum pressure of the pneumatic system. |
max_pressure=18.000000
max_pressure=0.000000
max_pressure = 21.5
max_pressure=0 |
bleed_air_scalar |
The ratio of bleed-air pressure from the engines to pneumatic air pressure in the pneumatic system. |
bleed_air_scalar=1.000000
bleed_air_scalar=0.000000
bleed_air_scalar=0.00000
bleed_air_scalar=0.150000 |
[exits]
The following parameters define the aircraft's exits:
Property
|
Description
|
Examples
|
number_of_exits |
This value defines the number of simulated exits, or
doors, on the aircraft. |
number_of_exits = 3
number_of_exits =1
number_of_exits = 1
number_of_exits = 2 |
exit.0
to
exit.n |
Five values: the open and close rate percent per second
(where 1.0 is fully open), the position relative to datum reference point, and the type of
exit, one of:
0 = Main
1 = Cargo
2 = Emergency |
exit.0 = 0.4, 40.50,-6.0, 7.0, 0
exit.0 = 0.4, 41.3, -6.0, 4.0, 0
exit.0 = 0.4, -30.30, -9.5, 1, 0
exit.0 = 0.4, -16.50, -4.5, 0.5, 0
exit.1 = 0.4, -74.00, -4.5, 0.5, 1
exit.2 = 0.4, -36.50, -2.5, -1.0, 1 |
[effects]
The effects section of the file refers to the visual
effects that result from various systems or reactions of the aircraft.
An effect file associated with a keyword in this section will be used
when the corresponding action is triggered. If no
entry is made a default effect file will be used. The table below
outlines the aircraft effects currently
supported, though of course not all effects are supported on 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 |
wake=fx_wake |
water |
The landing, taxiing or taking off from water effect. |
fx_spray |
False |
water=fx_spray |
waterspeed |
Traveling at speed on the water. |
fx_spray |
False |
|
dirt |
Moving on dirt. |
fx_tchdrt |
False |
dirt=fx_tchdrt |
concrete |
Moving on concrete. |
fx_sparks |
False |
concrete=fx_sparks
concrete=fx_tchdwn_s |
touchdown |
The touchdown effect, which usually is followed by an
optional 1 to indicate the effect is to be run once only. |
fx_tchdwn |
True |
touchdown=fx_tchdwn, 1
touchdown=fx_tchdwn_s, 1 |
contrail |
Contrail effect, applies to jets flying above 29000ft. |
fx_contrail_l |
False |
|
startup |
Engine startup. |
fx_engstrt |
True |
startup=fx_engstrt_jenny
startup=fx_engstrt_cub |
landrotorwash |
Rotor wash. Helicopters only. |
fx_rtr_lnd |
False |
waterrotorwash |
Water rotor wash. Helicopters only. |
fx_rtr_wtr |
False |
vaportrail_l |
Left wing vapor trail. |
fx_vaportrail_l |
False |
vaportrail_r |
Right wing vapor trail. |
fx_vaportrail_r |
False |
l_wingtipvortice |
Left wingtip vortice (contrails off the wingtip, usually from a jet such as the F18). |
fx_wingtipvortice_l |
True |
r_wingtipvortice |
Right wingtip vortice. |
fx_wingtipvortice_r |
True |
fueldump |
Fuel dump active. |
No default effect |
False |
EngineFire |
Engine fire. |
fx_engfire |
False |
EngineFire=fx_heliFire |
EngineDamage |
Engine damage. |
fx_engsmoke |
False |
EngineOilLeak |
Oil leak. |
fx_OilLeak |
False |
SkidPavement |
Skid on tarmac, leaves a mark. |
fx_skidmark |
False |
SnowSkiTrack |
Skid on snow. |
No default effect |
False |
SnowTrack = fx_snowtrack |
WheelSnowSpray |
Taking off on snow. |
fx_WheelSnowSpray |
False |
WheelSnowSpray = fx_WheelSnowSpray |
WheelWetSpray |
Taking off on wet runway. |
fx_WheelWetSpray |
False |
WheelWetSpray = fx_WheelWetSpray |
WetEngineWash |
Similar to waterrotorwash, the effect a propeller has on wet terrain when flying below 20m. |
fx_WetEngineWash |
False |
SnowEngineWash |
Similar to waterrotorwash, the effect a propeller has on snow covered terrain, or when it is snowing, when flying below 20m. |
fx_SnowEngineWash |
False |
WaterBallastDrain |
Draining the water ballast, applies only to sailplanes. |
fx_WaterBallastDrain |
False |
PistonFailure |
One or more pistons failed. |
fx_PistonFailure |
True |
|
windshield_rain_effect_available |
Special case, set this to 0 to turn off the effect of rain on the windshield. |
|
|
windshield_rain_effect_available = 0 |
[autopilot]
The following parameters determine the functionality of 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. |
autopilot_available=1
autopilot_available=0 |
flight_director_available |
Setting this flag to a 1 makes available a
flight director on the aircraft. |
flight_director_available=1
flight_director_available=0 |
default_vertical_speed |
The default vertical speed, in feet per second, that
the autopilot will command when selecting a large altitude change. |
default_vertical_speed=1800
default_vertical_speed = 1800.0
default_vertical_speed= 700.0
default_vertical_speed= 1800.0 |
autothrottle_available |
Setting this flag to a 1 makes available
an autothrottle system on the aircraft. |
autothrottle_available = 1
autothrottle_available= 0 |
autothrottle_arming_required |
Setting this flag to 1 will require that the
autothrottle be armed prior to it being engaged.
Setting it to zero allows the autothrottle to be engaged directly. |
autothrottle_arming_required
= 1
autothrottle_arming_required= 0 |
autothrottle_max_rpm |
This sets the maximum engine speed, in percent, that
the autothrottle will attempt to maintain. |
autothrottle_max_rpm = 90
autothrottle_max_rpm = 90 |
autothrottle_takeoff_ga |
Setting this flag to 1 enables takeoff / go-around
operations with the autothrottle. |
autothrottle_takeoff_ga = 1
autothrottle_takeoff_ga= 0
|
default_pitch_mode |
This
determines the default pitch mode when the autopilot logic is turned on.
0 = None
1 = Pitch Hold (current pitch angle)
2 = Altitude Hold (current altitude)
If no value is set, Pitch Hold will be the default. |
|
pitch_takeoff_ga |
The default pitch that the Takeoff/Go-Around mode
references. |
pitch_takeoff_ga=8.0
pitch_takeoff_ga=0.0 |
max_pitch |
The maximum pitch angle in degrees that the autopilot
will command either up or down. |
max_pitch=10.0
|
max_pitch_acceleration |
The maximum angular pitch acceleration, in degrees per
second squared, that the autopilot will command up or down. |
max_pitch_acceleration=1.0
|
max_pitch_velocity_lo_alt |
The maximum angular pitch velocity, in degrees per
second, which the autopilot will command when at an altitude below that
specified by the variable max_pitch_velocity_lo_alt_breakpoint. |
max_pitch_velocity_lo_alt=2.0
|
max_pitch_velocity_hi_alt |
The maximum angular pitch velocity, in degrees per
second, which the autopilot will command when at an altitude above the
altitude specified by the variable
max_pitch_velocity_hi_alt_breakpoint. The maximum velocity is
interpolated between the hi and lo altitude velocities when between the
hi and lo altitude breakpoints. |
max_pitch_velocity_hi_alt=1.5
|
max_pitch_velocity_lo_alt_breakpoint |
The altitude below which the autopilot maximum pitch
velocity is limited by the variable max_pitch_velocity_lo_alt. |
max_pitch_velocity_lo_alt_breakpoint=20000.0
|
max_pitch_velocity_hi_alt_breakpoint |
The altitude above which the autopilot maximum pitch
velocity is limited by the variable max_pitch_velocity_hi_alt. The
maximum velocity is interpolated between the hi and lo altitude
velocities when between the hi and lo altitude breakpoints. |
max_pitch_velocity_hi_alt_breakpoint=28000.0
|
max_bank |
The maximum bank angle in degrees that the autopilot
will command either left or right.
|
max_bank=25.0
max_bank=30,25,20,15,10
max_bank=30,15
max_bank=25.000000 |
max_bank_acceleration |
The maximum angular bank acceleration, in degrees per
second squared, that the autopilot will command left or right. |
max_bank_acceleration=1.8
|
max_bank_velocity |
The maximum angular bank velocity, in degrees per
second, which the autopilot will command left or right. |
max_bank_velocity=3.000000 |
max_throttle_rate |
This value sets the maximum rate at which the
autothrottle will move the throttle position. In the example, the
maximum rate is set to 10% of the total throttle range per second. |
max_throttle_rate=0.100000 |
nav_proportional_control |
Proportional controller constant in lateral navigation
modes. |
nav_proportional_control=12.00
nav_proportional_control=16.00
nav_proportional_control=9.00
nav_proportional_control=11.00 |
nav_integrator_control |
Integral controller constant in lateral navigation
modes. |
nav_integrator_control=0.25
nav_integrator_control=0.17
nav_integrator_control=0.20
nav_integrator_control=0.250000 |
nav_derivative_control |
Derivative controller constant in lateral navigation
modes. |
nav_derivative_control=0.00
nav_derivative_control=0.000000 |
nav_integrator_boundary |
The boundary, or maximum signal error, in degrees in
which the integrator function is active. In the example, the integrator
is active when the error is between -2.5 and +2.5 degrees from the
centerline of the navigation signal. |
nav_integrator_boundary=2.50
|
nav_derivative_boundary |
The boundary, or maximum signal error, in degrees in
which the derivative function is active. In the example, the derivative
controller is not active because the maximum error is set to 0. |
nav_derivative_boundary=0.00
|
gs_proportional_control |
Proportional controller constant in glideslope mode. |
gs_proportional_control=25.0
gs_proportional_control = 18.0
gs_proportional_control=9.52
gs_proportional_control=9.520000 |
gs_integrator_control |
Integral controller constant in glideslope mode. |
gs_integrator_control=0.53
gs_integrator_control = 0.33
gs_integrator_control=0.26
gs_integrator_control=0.260000 |
gs_derivative_control |
Derivative controller constant in glideslope mode. |
gs_derivative_control = 0.00
|
gs_integrator_boundary |
The boundary, or maximum signal error, in degrees in
which the glideslope integrator function is active. In the example, the
integrator is active when the error is between -0.7 and +0.7 degrees
from the centerline of the glideslope signal. |
gs_integrator_boundary = 0.70
|
gs_derivative_boundary |
The boundary, or maximum signal error, in degrees in
which the derivative function is active. In the example, the derivative
controller is not active because the maximum error is set to 0. |
gs_derivative_boundary = 0.00
|
yaw_damper_gain |
The proportional gain on the yaw dampers yaw rate
error. |
yaw_damper_gain = 1.0
yaw_damper_gain = 0.0 |
direction_indicator |
Indicates which direction indicator system on the
aircraft is being referenced by the autopilot.
0 = the first, and is
the default. |
direction_indicator=1 |
attitude_indicator |
Indicates which attitude indicator system on the
aircraft is being referenced by the autopilot.
0 = the first, and is
the default. |
attitude_indicator =1 |
default_bank_mode |
This determines the default bank mode when the
autopilot logic is turned on.
0 = None
1 = Wing Level Hold
2 =
Heading Hold (current heading).
If no value is set, Wing Level Hold
will be the default. |
default_bank_mode=2 |
[fuel]
This section defines the characteristics of the fuel system,
including the tanks, fuel type, and the number of 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. |
Center1 = -83.5, 0.0, -7.0,
17164.0, 0.0
Center1 = -48.7, 0.0, -4.0, 982.0, 0.0
Center2 = -193.5, 0.0, 6.0,
3300.0, 0.0
Center3=-10.600000,0.000000,-1.900000,25.000000,0.000000
LeftMain = -3, -19, 0, 1500, 0
RightMain = -8.46, 6.45, 0.0, 71.0, 0.0
LeftAux = -2.24, -11.4, 2.40, 15.0, 0.00
|
fuel_type |
One of:
1 = Avgas
2 = JetA |
fuel_type = 2
fuel_type = 1
|
number_of_tank_selectors |
Number of fuel tank selectors (maximum 4 and should be
less
than or equal to the number of engines). |
number_of_tank_selectors=1
number_of_tank_selectors = 2 |
electric_pump |
Boolean that sets whether an electric boost pump is
available, 0 = FALSE, 1 = TRUE. |
electric_pump=0
electric_pump = 1 |
fuel_dump_rate |
Percent of fuel that can be dumped per second. |
fuel_dump_rate = 0.0167 |
engine_driven_pump |
Set to 0 if the pump is engine driven (1 is the
default). |
engine_driven_pump=0
engine_driven_pump=1 |
manual_pump |
Set to 1 if there is a manual transfer pump. |
manual_transfer_pump=1 |
anemometer_pump |
Set
to 1 if there is an anemometer pump. |
anemometer_pump=1 |
[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). |
wing_area = 1137.0
wing_area= 150.000
wing_area = 5825.0
wing_area = 199.0 |
wing_span |
Wing span is the horizontal distance from wing-tip to
wing-tip (feet). |
wing_span = 94.75
wing_span= 30.000
wing_span = 211.4
wing_span = 37.8 |
wing_root_chord |
Length of the wing chord (leading edge to trailing
edge) at the intersection of the wing and the fuselage (feet). |
wing_root_chord = 18.0
wing_root_chord= 5.000
wing_root_chord = 48.8
wing_root_chord = 5.3 |
wing_dihedral |
When looking at the front of an aircraft, this is the
angle between the wing leading edge and a horizontal line parallel to
the ground (degrees). |
wing_dihedral = 6.2
wing_dihedral= 7.998
wing_dihedral = 7.0
wing_dihedral = 6.9 |
wing_incidence |
When looking at the side of an aircraft from the 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. |
wing_incidence = 1.0
wing_incidence= 0.000
wing_incidence = 2.0
wing_incidence = 1.5 |
wing_twist |
This is the difference in wing incidence from the root
chord and the tip chord of the wing, (degrees). Also known as wash-out. |
wing_twist = -0.5
wing_twist= -1.000
wing_twist = -1.0
wing_twist = -1.5 |
oswald_efficiency_factor |
This is a measure of the aerodynamic efficiency of the
wing. A theoretically perfect wing will have a factor of 1.0. |
oswald_efficiency_factor=
0.750
oswald_efficiency_factor= 0.68
oswald_efficiency_factor= 0.7 |
wing_winglets_flag |
Boolean to indicate if the aircraft incorporates the
use of winglets; 0 = FALSE, 1 = TRUE. |
wing_winglets_flag= 0
wing_winglets_flag = 1 |
wing_sweep |
When looking down on top of an aircraft, this is the
angle the wing leading edge makes with a horizontal line perpendicular
to the fuselage, (degrees). |
wing_sweep = 25.0
wing_sweep = 37.5
wing_sweep = 0.0 |
wing_pos_apex_lon |
Longitudinal distance of the wing apex (measured at
centerline of aircraft) from defined reference point (feet). This
distance is measured positive in the forward (out the aircraft nose)
direction. |
wing_pos_apex_lon = 8.0
wing_pos_apex_lon= 0.000
wing_pos_apex_lon = -58.2
wing_pos_apex_lon = -5.6 |
wing_pos_apex_vert |
Vertical distance of the wing apex (measured at
centerline of aircraft) from defined reference point (feet). This
distance is measured positive in the up direction. |
wing_pos_apex_vert = 0
wing_pos_apex_vert = -3.6 |
htail_area |
Area of the top surface of the entire horizontal tail
(tip-to-tip) (ft2). |
htail_area = 338.0
htail_area= 28.000
htail_area = 1470
htail_area = 60.0 |
htail_span |
Horizontal tail span is the horizontal distance from
horizontal tail-tip to horizontal tail -tip (feet). |
htail_span = 41.7
htail_span= 7.917
htail_span = 72.8
htail_span = 15.9 |
htail_pos_lon |
Longitudinal distance of the horizontal tail apex
(measured at centerline of aircraft) from defined reference point
(feet). This distance is measured positive in the forward (out the
aircraft nose) direction. |
htail_pos_lon = -35.0
htail_pos_lon= -11.417
htail_pos_lon = -210.0
htail_pos_lon = -20.1 |
htail_pos_vert |
Vertical distance of the horizontal tail apex (measured
at centerline of aircraft) from defined reference point, (feet). This
distance is measured positive in the up direction. |
htail_pos_vert = 0.0
htail_pos_vert = 12.7
htail_pos_vert = 0.9 |
htail_incidence |
When looking at the side of an aircraft from the
horizontal tail tip, this is the angle the mean horizontal tail chord
makes with a horizontal line parallel to the ground (degrees). |
htail_incidence= 0.000
htail_incidence = 0.5
htail_incidence = 4.0 |
htail_sweep |
When looking down on top of an aircraft, this is the
angle the horizontal tail leading edge makes with a horizontal line
perpendicular to the fuselage (degrees). |
htail_sweep = 30.0
htail_sweep = 37.5
htail_sweep = 0.0 |
vtail_area |
Area of the surface of one side of the vertical tail
(fuselage-to-tip) (ft2). |
vtail_area = 224.0
vtail_area= 7.000
vtail_area = 1060
vtail_area = 88.0 |
vtail_span |
Vertical tail span is the vertical distance from the
vertical tail-fuselage intersection to the tip of the vertical tail
(feet). |
vtail_span = 20.0
vtail_span= 3.017
vtail_span = 37.1
vtail_span = 10.7 |
vtail_sweep |
When looking at the side of the vertical tail, this is
the angle the vertical tail leading edge makes with a vertical line
perpendicular to the fuselage (degrees). |
vtail_sweep = 35.0
vtail_sweep = 45.0
vtail_sweep = 0.0 |
vtail_pos_lon |
Longitudinal distance of the vertical tail apex
(measured at centerline of aircraft) from defined reference point,
(feet). This distance is measured positive in the forward (out the
aircraft nose) direction. |
vtail_pos_lon = -35.8
vtail_pos_lon= -11.417
vtail_pos_lon = -198.5
vtail_pos_lon = -22.9 |
vtail_pos_vert |
Vertical distance of the vertical tail apex (measured
at centerline of aircraft) from defined reference point (feet). This
distance is measured positive in the up direction. |
vtail_pos_vert = 5.8
vtail_pos_vert= 1.500
vtail_pos_vert = 26.1
vtail_pos_vert = 3.1 |
elevator_area |
Area of the top surface of the entire elevator
(tip-to-tip) (ft2). |
elevator_area = 70.5
elevator_area= 12.040
elevator_area = 327
elevator_area = 20.0 |
aileron_area |
Area of the top surface of all the ailerons on the wing
(ft2). |
aileron_area = 26.9
aileron_area= 15.000
aileron_area = 225
aileron_area = 11.3 |
rudder_area |
Area of the side surface of the entire rudder (ft2). |
rudder_area = 56.2
rudder_area= 2.450
rudder_area = 230
rudder_area = 10.5 |
elevator_up_limit |
Angular limit of the elevator when deflected up
(degrees). |
elevator_up_limit = 22.5
elevator_up_limit= 27.502
elevator_up_limit = 25
elevator_up_limit = 17.0 |
elevator_down_limit |
Angular limit of the elevator when deflected down
(degrees). |
elevator_down_limit = 19.5
elevator_down_limit= 20.626
elevator_down_limit = 15
elevator_down_limit = 15.5 |
aileron_up_limit |
Angular limit of the aileron when deflected up
(degrees). |
aileron_up_limit = 20.0
aileron_up_limit= 19.481
aileron_up_limit = 25
aileron_up_limit = 18.0 |
aileron_down_limit |
Angular limit of the aileron when deflected down
(degrees). |
aileron_down_limit = 20.0
aileron_down_limit= 14.897
aileron_down_limit = 15
aileron_down_limit = 18.0 |
rudder_limit |
Angular limit of the rudder deflection (degrees). |
rudder_limit = 26.0
rudder_limit= 23.491
rudder_limit = 31.5
rudder_limit = 30.0 |
elevator_trim_limit |
Angular limit of the elevator trim tab (degrees). |
elevator_trim_limit = 20.0
elevator_trim_limit= 20.000
elevator_trim_limit = 20
elevator_trim_limit = 15.0 |
spoiler_limit |
Angular limit of the wing spoilers on an aircraft,
(degrees). If this limit is zero, no spoilers exist for the aircraft. |
spoiler_limit = 60.0
spoiler_limit= 59.989
spoiler_limit = 45
spoiler_limit = 0.0 |
spoiler_extension_time |
Spoiler extension time in seconds. |
spoiler_extension_time = 2.0
spoiler_extension_time=5.000000
spoiler_extension_time = 0.2
spoiler_extension_time = 1.0 |
spoilerons_available |
Boolean to indicate if the spoilers also behave as
spoilerons for roll control (if spoilers are available): 0 = FALSE, 1 =
TRUE. |
spoilerons_available = 1
spoilerons_available= 0
spoilerons_available = 0 |
aileron_to_spoileron_gain |
If spoilerons are available, this value is the constant
used in determining the amount of spoiler deflection per aileron
deflection. |
aileron_to_spoileron_gain = 3
aileron_to_spoileron_gain = 0
aileron_to_spoileron_gain = 4.6 |
min_ailerons_for_spoilerons |
This value indicates at what aileron deflection the
spoilers are become active for roll control, (degrees). |
min_ailerons_for_spoilerons = 10
min_ailerons_for_spoilerons = 0
min_ailerons_for_spoilerons = 5 |
min_flaps_for_spoilerons |
This value indicates at what minimum flap handle
position the spoilerons become active. |
min_flaps_for_spoilerons=
0.0 |
auto_spoiler_available |
Set to 1 if auto spoiler is available. |
auto_spoiler_available = 1
auto_spoiler_available = 0 |
positive_g_limit_flaps_up |
Design g load tolerance (flaps up). |
positive_g_limit_flaps_up = 4.0
positive_g_limit_flaps_up = 3.0
positive_g_limit_flaps_up = 5.5 |
positive_g_limit_flaps_down |
Design g load tolerance (flaps down). |
positive_g_limit_flaps_down= 3.0
positive_g_limit_flaps_down=2.000000
positive_g_limit_flaps_down= 5.5 |
negative_g_limit_flaps_up |
Design g load tolerance (negative, flaps up). |
negative_g_limit_flaps_up = -3.0
negative_g_limit_flaps_up = -2.0
negative_g_limit_flaps_up = -1.5 |
negative_g_limit_flaps_down |
Design g load tolerance (negative, flaps down). |
negative_g_limit_flaps_down= -2.0
negative_g_limit_flaps_down= -1.5
negative_g_limit_flaps_down= -3.5 |
load_safety_factor |
Design g load safety factor. |
load_safety_factor = 1.5 |
fly_by_wire |
Fly by wire system available. |
fly_by_wire = 1 |
spoiler_handle_available |
Boolean that configures the airplane with manual
control of the spoiler deflections. 0 = FALSE, 1 = TRUE. |
spoiler_handle_available
= 0 |
flap_to_aileron_scale |
Flaperons - deflection of ailerons due to flap
deflection. |
flap_to_aileron_scale
= 0.3
flap_to_aileron_scale = 0.5 |
aileron_to_rudder_scale |
Link
the rudder to aileron input. |
aileron_to_rudder_scale = 0.4 |
[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). |
flaps_up_stall_speed = 142.0
flaps_up_stall_speed= 24.000
flaps_up_stall_speed = 140.0
flaps_up_stall_speed = 84.0 |
full_flaps_stall_speed |
Stall speed of the aircraft in a dirty (flaps full
down) configuration at standard sea level conditions, (Knots True
Airspeed, KTAS). |
full_flaps_stall_speed = 113.0
full_flaps_stall_speed= 24.000
full_flaps_stall_speed = 112.0
full_flaps_stall_speed = 75.0 |
cruise_speed |
Typical cruise speed of the aircraft in a clean (flaps
up) configuration at a typical cruise altitude, (Knots True Airspeed,
KTAS). |
cruise_speed = 477.0
cruise_speed= 84.560
cruise_speed = 505.0
cruise_speed = 180.0 |
max_mach |
Maximum design mach of the aircraft. This generally
only applies to turbine airplanes. |
max_mach = 0.82
max_mach = 0.92
max_mach = 0.58
max_mach = 0.83 |
max_indicated_speed |
Maximum design indicated airspeed. Also referred to as
Never Exceed Speed or Red Line of the aircraft, (Knots Indicated
Airspeed). |
max_indicated_speed = 340
max_indicated_speed=65.000000
max_indicated_speed = 365.0
max_indicated_speed = 223 |
[forcefeedback]
As detailed in the tables below, the parameters in 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.
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. |
gear_bump_nose_magnitude=3000
gear_bump_nose_magnitude=6000 |
gear_bump_nose_direction |
Integer from 0 - 35999 degrees. |
gear_bump_nose_direction=18000 |
gear_bump_nose_duration |
Integer, microseconds. |
gear_bump_nose_duration=250000 |
gear_bump_left_magnitude |
Integer from 0 - 10000. |
gear_bump_left_magnitude=2700
gear_bump_left_magnitude=6000 |
gear_bump_left_direction |
Integer from 0 - 35999 degrees. |
gear_bump_left_direction=35500
gear_bump_left_direction=9000 |
gear_bump_left_duration |
Integer, microseconds. |
gear_bump_left_duration=250000 |
gear_bump_right_magnitude |
Integer from 0 - 10000. |
gear_bump_right_magnitude=2700
gear_bump_right_magnitude=6000 |
gear_bump_right_direction |
Integer from 0 - 35999 degrees. |
gear_bump_right_direction=00500
gear_bump_right_direction=27000 |
gear_bump_right_duration |
Integer, microseconds. |
gear_bump_right_duration=250000 |
ground_bumps_magnitude1 |
Integer from 0 - 10000. |
ground_bumps_magnitude1=1300
ground_bumps_magnitude1=3250
ground_bumps_magnitude1=2500
ground_bumps_magnitude1=2600 |
ground_bumps_angle1 |
Integer from 0 - 35999 degrees. |
ground_bumps_angle1=8900 |
ground_bumps_intercept1 |
Floating point number, from 0 to 1,000,000 cycles
per second. |
ground_bumps_intercept1=3.0
ground_bumps_intercept1=5.0
ground_bumps_intercept1=10.0
ground_bumps_intercept1=4.0 |
ground_bumps_slope1 |
Floating point number, from 0 to 1,000,000 cycles
per second. |
ground_bumps_slope1=0.20
ground_bumps_slope1=0.48
ground_bumps_slope1=0.300
ground_bumps_slope1=0.6 |
ground_bumps_magnitude2 |
Integer from 0 - 10000. |
ground_bumps_magnitude2=200
ground_bumps_magnitude2=750
ground_bumps_magnitude2=350
ground_bumps_magnitude2=1200 |
ground_bumps_angle2 |
0 - 35999 degrees. |
ground_bumps_angle2=09100
ground_bumps_angle2=9100 |
ground_bumps_intercept2 |
Floating point number, from 0 to 1,000,000 cycles
per second. |
ground_bumps_intercept2=1.075
ground_bumps_intercept2=0.075
ground_bumps_intercept2 =1.075
ground_bumps_intercept2=0.085 |
ground_bumps_slope2 |
Floating point number, from 0 to 1,000,000 cycles
per second. |
ground_bumps_slope2=0.035
ground_bumps_slope2=1.0
ground_bumps_slope2=0.65 |
crash_magnitude1 |
Sets the magnitude of the first force, from 0 to 10000.
|
crash_magnitude1=10000 |
crash_direction1 |
Sets the direction from which first force is felt, from
0 to 35999. |
crash_direction1=01000 |
crash_magnitude2 |
Sets the initial magnitude of the second force, from 0
to 10000. |
crash_magnitude2=10000 |
crash_direction2 |
Sets the direction from which the second force is felt,
from 0 to 35999. |
crash_direction2=9000 |
crash_period2 |
Determines the frequency (frequency = 1/period) of the
second crash force, in microseconds. |
crash_period2=75000 |
crash_duration2 |
Sets the amount of time that the second crash force is
felt, in microseconds. |
crash_duration2=2500000
crash_duration2=3500000 |
stick_shaker_magnitude |
Integer from 0 - 10000. |
stick_shaker_magnitude=5000 |
stick_shaker_direction |
Integer from 0 - 35999 degrees. |
stick_shaker_direction=0 |
stick_shaker_period |
In microseconds. |
stick_shaker_period=111111 |
[stall_warning]
This section defines the stall warning system of the aircraft.
Property
|
Description
|
Examples
|
type |
This flag determines the type of stall warning system,
one of:
0 = None
1 = Suction
2 = Electric |
type=2
type=0
type=1 |
stick_shaker |
Set to 1 if the aircraft has a stick shaker. |
stick_shaker=1
stick_shaker=0 |
[deice_system]
This section defines the deice system of the aircraft.
Property
|
Description
|
Examples
|
structural_deice_type |
Type of deicer, of one:
0 = None
1 = Heated Leading Edge
2 = Bleed Air Boots
3 = Eng Pump Boots. |
structural_deice_type=1
structural_deice_type=0
structural_deice_type=3
structural_deice_type=2 |
[piston_engine]
A piston engine’s power can be determined through 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 the simulation needs 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” value.
Property
|
Description
|
Examples
|
detonation_onset |
The manifold pressure that if reached or exceeded will lead to the engine detonating. |
detonation_onset = 36
detonation_onset = 80 |
supercharged |
On/off. |
supercharged=1 |
supercharger_boost |
Multiplier on manifold pressure if supercharger is engaged.. |
supercharger_boost=1.20 |
supercharger_power_cost |
Percent of horsepower required to drive supercharger. |
supercharger_power_cost=0.22 |
emergency_boost_duration |
Emergency boost duration in seconds. The emergency boost system was designed to model the systems used on WWII aircraft. The nitrous and supercharging systems are available for more modern aircraft.
|
emergency_boost_duration=0 |
max_rpm_mechanical_efficiency_scalar |
Scalar value that can be modified to tune the
mechanical efficiency of the engine at maximum rpm. Increase this value
to increase the mechanical efficiency, decrease it to decrease the
mechanical efficiency. |
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. |
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. |
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). |
idle_rpm_friction_scalar=1.000
|
cylinder_displacement |
Cubic inches per cylinder displacement. |
cylinder_displacement=
55.000
cylinder_displacement= 91.7
cylinder_displacement= 90.0
cylinder_displacement= 109.4 |
two_stroke_cycle |
Two stroke engine. |
two_stroke_cycle = 1 |
compression_ratio |
Compression ratio of each cylinder. |
compression_ratio= 11.500
compression_ratio= 8.0
compression_ratio= 8.5
compression_ratio= 6.0 |
number_of_cylinders |
Integer value; number of cylinders in the engine. |
number_of_cylinders= 2
number_of_cylinders= 6
number_of_cylinders=4
number_of_cylinders=9 |
max_rated_rpm |
Maximum rated revolutions per minute (RPM) of the
engine (red line). |
max_rated_rpm= 5500.000
max_rated_rpm= 2700.0
max_rated_rpm= 2700
max_rated_rpm= 2300 |
max_rated_hp |
Maximum rated brake horsepower output of the engine. |
max_rated_hp= 53.600
max_rated_hp= 300.0
max_rated_hp= 180
max_rated_hp= 450 |
fuel_metering_type |
Integer value indicating the fuel metering type, one of:
0 =
Fuel Injected
1 = Gravity Carburetor,
2 = Aerobatic Carburetor. |
fuel_metering_type= 1
fuel_metering_type= 0
fuel_metering_type = 1 |
cooling_type |
Integer value indicating the method of engine cooling,
one of:
0 = air cooled
1 = liquid cooled. |
cooling_type= 1
cooling_type= 0 |
normalized_starter_torque |
This value can be modified to increase/decrease 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. |
normalized_starter_torque= 0.3 |
turbocharged |
Boolean to indicate if the engine is turbocharged; 0 =
FALSE, 1 = TRUE. |
turbocharged= 0
turbocharged= 1 |
max_design_mp |
If a turbocharger is present, this value indicates the
maximum design manifold pressure supplied by the turbocharger (inHg). |
max_design_mp= 0.0
max_design_mp= 36.5 |
min_design_mp |
If a turbocharger is present, this value indicates the
minimum design manifold pressure of the turbocharger (inHg). |
min_design_mp= 1.0
min_design_mp= 10 |
critical_altitude |
Altitude to which the turbocharger, if present, will
provide the maximum design manifold pressure (feet). |
critical_altitude= 0.0
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). |
emergency_boost_type= 0 |
emergency_boost_mp_offset |
Additional manifold pressure supplied by emergency
boost, if available. |
emergency_boost_mp_offset=
0.000 |
emergency_boost_gain_offset |
Multiplier on manifold pressure due to emergency boost. |
emergency_boost_gain_offset=
0.000 |
fuel_air_auto_mixture |
Boolean to indicate if automatic fuel-to-air mixture is
available; 0 = FALSE, 1 = TRUE. |
fuel_air_auto_mixture= 0 |
auto_ignition |
Boolean to indicate if automatic ignition is available;
0 = FALSE, 1 = TRUE. |
auto_ignition= 0 |
power_scalar |
Changing this value affects the amount of power
delivered by the engine to the propellor shaft. |
power_scalar = 1.0 |
bestpowerspecificfuelconsumption |
Specific fuel consumption at Best Power mixture ratio. |
BestPowerSpecificFuelConsumption=0.49 |
magneto_order_left_right_both |
Sets the order of the magneto switch direction. |
magneto_order_left_right_both =
1 |
number_of_magnetos |
Number
of magnetos. |
number_of_magnetos = 1 |
[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. |
propeller_type= 1
propeller_type= 0
propeller_type = 0 |
propeller_diameter |
Diameter of propeller blades, tip to tip, in feet. |
propeller_diameter= 5.000
propeller_diameter= 6.4
propeller_diameter = 8.8
propeller_diameter= 6.3 |
propeller_blades |
Integer value indicating the number of blades on the
propeller (2, 3 or 4). |
propeller_blades= 2
propeller_blades= 3
propeller_blades = 4
propeller_blades = 3 |
propeller_moi |
Propeller moment of inertia, (slug ft2). |
propeller_moi= 3.000
propeller_moi= 6.9
propeller_moi = 24
propeller_moi= 5.0 |
beta_max |
Maximum blade pitch angle for constant speed prop
(degrees). (Not used if fixed pitch.). |
beta_max= 0
beta_max= 45.0
beta_max = 45
beta_max= 24.0 |
beta_min |
Minimum blade pitch angle for constant speed prop
(degrees). (Not used if fixed pitch.). |
beta_min= 0
beta_min= 15.2
beta_min = 15.2
beta_min = 15.6 |
min_gov_rpm |
The minimum rpm controlled by the governor for a
constant speed prop. |
min_gov_rpm= 0
min_gov_rpm= 1100.0
min_gov_rpm = 25520
min_gov_rpm= 800 |
prop_tc |
Time constant for prop. |
prop_tc= 0.100
prop_tc= 0.1
prop_tc = 0.004
prop_tc= 0 |
gear_reduction_ratio |
The reduction ratio from the engine output rpm to prop
rpm. |
gear_reduction_ratio= 1.000
gear_reduction_ratio= 1.0
gear_reduction_ratio = 17.6
gear_reduction_ratio = 17.4 |
fixed_pitch_beta |
Blade pitch angle for fixed pitch prop (degrees). (Not
used if constant speed.). |
fixed_pitch_beta= 28.000
fixed_pitch_beta= 0.0
fixed_pitch_beta = 0
fixed_pitch_beta= 20 |
low_speed_theory_limit |
The speed at which low-speed propeller theory gets
blended into the high speed propeller theory, (feet/second). |
low_speed_theory_limit=
80.000
low_speed_theory_limit= 80.0
low_speed_theory_limit = 80 |
prop_sync_available |
Boolean to indicate if propeller-sync is available
(twin engine aircraft); 0 = FALSE, 1 = TRUE. |
prop_sync_available= 0
prop_sync_available= 1
prop_sync_available = 1
prop_sync_available = 0 |
prop_deice_available |
Boolean to indicate if propeller de-icing is available;
0 = FALSE, 1 = TRUE. |
prop_deice_available= 0
prop_deice_available= 1
prop_deice_available = 1 |
prop_feathering_available |
Boolean to indicate if prop feathering is available
(constant speed prop only); 0 = FALSE, 1 = TRUE. |
prop_feathering_available= 0
prop_feathering_available= 1 |
prop_auto_feathering_available |
Boolean to indicate if prop auto-feathering is
available (constant speed prop only); 0 = FALSE, 1 = TRUE. |
prop_auto_feathering_available=
0
prop_auto_feathering_available= 1 |
min_rpm_for_feather |
Minimum rpm at which the prop will feather (if
feathering is available). |
min_rpm_for_feather= 700.0
min_rpm_for_feather = 700
min_rpm_for_feather= 0 |
beta_feather |
Propeller pitch angle when feathered (degrees). |
beta_feather= 82.5
beta_feather = 79.3
beta_feather= 0 |
power_absorbed_cf |
Coefficient of friction power absorbed by propeller. |
power_absorbed_cf=
0.9
power_absorbed_cf = 0.9
power_absorbed_cf= 0 |
defeathering_accumulators_available |
Boolean to indicate if de-feathering accumulators are
available; 0 = FALSE, 1 = TRUE. |
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. |
prop_reverse_available= 0
prop_reverse_available = 1 |
minimum_on_ground_beta |
Minimum blade pitch angle when the aircraft is on the
ground (degrees). |
minimum_on_ground_beta=
0.000
minimum_on_ground_beta= 0.0
minimum_on_ground_beta = 1.0
minimum_on_ground_beta= 0 |
minimum_reverse_beta |
Minimum blade pitch angle when the propeller is in
reverse (degrees). |
minimum_reverse_beta= 0.000
minimum_reverse_beta= 0.0
minimum_reverse_beta = -14.0
minimum_reverse_beta= 0 |
thrust_scalar |
Parameter that scales the calculated thrust provided by
the propeller. |
thrust_scalar=1.000
thrust_scalar = 1.0
thrust_scalar = 1.0 |
feathering_switches |
Boolean indicating if feathering switches are
available. 0 = FALSE, 1 = TRUE. Feathering switches, allow the pilot to automatically feather the propeller
via a switch, regardless of the propeller lever position. |
feathering_switches = 1 |
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). |
Compass.0 = 1 |
[gpws]
This section sepcifies the details of the ground proximity warning system.
Property
|
Description
|
Examples
|
max_warning_height |
The height below which a warning is activated. |
max_warning_height = 1000 |
sink_rate_fpm |
If an aircraft exceeds this rate of descent a warning is activated. |
sink_rate_fpm = -1500 |
excessive_sink_rate_fpm |
If an aircraft exceeds this rate of descent an urgent warning is activated. |
excessive_sink_rate_fpm = -2000 |
climbout_sink_rate_fpm |
If an aircraft starts to descend during takeoff, and exceeds this rate of descent, a warning is activated. |
climbout_sink_rate_fpm = -100 |
flap_and_gear_sink_rate_fpm |
If an aircraft is landing, and exceeds this rate of descent without flaps or gear extended, a warning is activated. |
flap_and_gear_sink_rate_fpm= -100 |
[cameradefinition.n]
This section shows the camera properties most used by aircraft.
An aircraft can have multiple cameradefinition sections, which 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 |
Title = "Right Side Window"
Title = "Right Wing"
Title = "Right Float"
Title = "Tail" |
guid |
Guid =
{54F54B8A-3EC2-2D4E-8D10-B8F9D0F16ACC}
Guid =
{C690EAFD-223A-42d0-99E0-681ADF93BB59} |
description |
Description = "View of the
right wing from the passenger cabin"
Description = "View from the right wing
tip looking at the cockpit"
Description = "View from the aft end
of the right float looking forward"
Description = "Looking forward from the tip of
the vertical stabilizer" |
origin |
Origin = Center
Origin = Virtual Cockpit |
snappbhadjust |
SnapPbhAdjust = Swivel
SnapPbhAdjust = None |
snappbhreturn |
SnapPbhReturn = FALSE |
panpbhadjust |
PanPbhAdjust = Swivel
PanPbhAdjust = None |
panpbhreturn |
PanPbhReturn = FALSE |
track |
Track = None |
showaxis |
ShowAxis = FALSE
ShowAxis = TRUE |
allowzoom |
AllowZoom = TRUE
AllowZoom = FALSE |
initialzoom |
InitialZoom = 1.0
InitialZoom = 0.75
InitialZoom = .5
InitialZoom = 0.4 |
showweather |
ShowWeather = Yes |
initialxyz |
InitialXyz = 5.5, 0.75, -13
InitialXyz = 7.5, 0.75, 0
InitialXyz = 1.5, .5, -3.9
InitialXyz = 0, 2.0, -3.9 |
initialpbh |
InitialPbh = 0, 0, 95
InitialPbh = 5, 0, 270
InitialPbh = 0, 0, 0
InitialPbh = 10, 0, 0 |
xyzadjust |
XyzAdjust = TRUE |
category |
Category=Aircraft
Category = VC |
momentumeffect |
MomentumEffect=TRUE
MomentumEffect = TRUE |
clipmode |
ClipMode=Minimum |
zoompanscalar |
ZoomPanScalar = 1.0 |
showlensflare |
ShowLensFlare=FALSE |
[turboprop_engine]
The amount of power generated by an engine and the 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 propellor shaft. |
power_scalar = 1.0
power_scalar = 1.0 |
maximum_torque |
Maximum shaft-torque available from the engine
(ft-lbs). |
maximum_torque = 3270
maximum_torque = 1865
maximum_torque = 7878 |
powerspecificfuelconsumption |
Brake power specific fuel consumption (turboprop only). |
PowerSpecificFuelConsumption = 0.55 |
[airspeed_indicators]
This section is used to define the characteristics of 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. |
airspeed_indicator.0 =
1.183, -24.75
airspeed_indicator.0 = 1, 0
airspeed_indicator.0 = 1.3, -24.0 |
[pressurization]
This section defines the presssurization characteristics of the
aircraft.
Property
|
Description
|
Examples
|
design_cabin_pressure |
|
design_cabin_pressure =
0 |
max_pressure_differential |
|
max_pressure_differential
= 0 |
[variometers]
This section defines the variometers characteristics of the aircraft.
Property
|
Description
|
Examples
|
variometer.0 |
|
variometer.0=1 |
[yaw_string]
This section defines the yaw string characteristics of the aircraft.
Property
|
Description
|
Examples
|
yaw_string_available |
|
yaw_string_available=1 |
[water
ballast system]
This section defines the water ballast system of the aircraft.
Property
|
Description
|
Examples
|
tank.0 |
Front Fuselage. |
Tank.0 = 7.79, -2.75, 0.0, 0.0, 1 |
tank.1 |
Rear Fuselage. |
Tank.1 = 3.57, -3.28, 0.0, 0.0, 2 |
tank.2 |
Left Outboard. |
Tank.2 = 9.25, -0.60, -10.5, 0.0, 2 |
tank.3 |
Left Inboard. |
Tank.3 = 16.38, -0.66, -4.5, 0.0, 1 |
tank.4 |
Right Inboard. |
Tank.4 = 16.38, -0.66, 4.5, 0.0, 1 |
tank.5 |
Right Outboard. |
Tank.5 = 9.25, -0.60, 10.5, 0.0, 2 |
numberofreleasevalves |
Number of release valves. |
NumberOfReleaseValves = 2 |
dumprate |
Gallons per second. |
DumpRate = 0.18494 |
[smokesystem]
The section describes how to configure a smoke system for 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. |
smoke.0=-10.00, -0.70, 0.0,
fx_smoke_w |
[folding_wings]
This section describes the folding wing characteristics of the aircraft. Note that these are folding wings used to store an aircraft more compactly when on the ground, or on deck, and not the variable sweep wings used on some supersonic aircraft. Variable sweep wings are not supported.
Property
|
Description
|
Examples
|
wing_fold_system_type |
One of:
0: None (the default)
1: Manual
2: Pneumatic
3: Electrical
4: Hydraulic
|
wing_fold_system_type = 1
wing_fold_system_type = 4
|
fold_rates |
Two values (for left and right), giving the percentage per second, to fully extend and retract. |
fold_rates = 0.25,0.20
fold_rates = 0.12,0.11
|
[anemometers]
This section describes the positions of the anemometers in the aircraft.
Property
|
Description
|
Examples
|
anemometer.0
to
anemometer.n |
Position of the anemometer relative to datum reference point. |
anemometer.0 = -10.0, 0.0, 2.7
anemometer.0 = 9.6, 0.0, -2.2 |
[realismconstants]
This section describes some realism constraints, dealing in particular with early aircraft. The values entered are used to make an aircraft more stable.
Property
|
Description
|
Examples
|
rollmomentfrombeta |
Scalar and offset applied to the roll moment from beta. |
RollMomentFromBeta = -0.5, 0 |
rollmomentfromailerons |
Scale and offset applied to the roll moment from the ailerons. |
RollMomentFromAilerons = 1.5, 0 |
pitchmomentzeroalpha |
Scale and offset applied to the zero angle of attack. |
PitchMomentZeroAlpha = 1.0, 0.002 |
Helicopter Specific Sections (Work in Progress)
The following sections are specific to helicopters only. These sections are a work in progress.
Additional Helicopter Sections
[sling.n]
There can be multiple sling positions on an aircraft, each with its own set of the following properties.
Property
|
Description
|
Examples
|
hoist_extend_rate |
Feet per second. |
hoist_extend_rate = 5 |
hoist_retract_rate |
Feet per second. |
hoist_retract_rate = -5 |
position |
Position relative to datum reference point. |
position = -34.7, 6.7, 7.0 |
max_stretch |
Max stretch distance at ultimate load. |
max_stretch = 2.0 |
damping_ratio |
0 for no damping to 1.0 for critically damped. |
damping_ratio = 0.6 |
rated_load |
Characteristics tension of cable in pounds. |
rated_load = 600 |
ultimate_load |
Breaking force in pounds. This cannot exceed 10,000lb. |
ultimate_load = 2250 |
tolerance_angle |
Angle, in degrees, used to determine lateral breaking force limit. |
tolerance_angle=45 |
auto_pickup_range |
Max Range, in feet, for auto-pickup. |
auto_pickup_range = 8 |
auto_pickup_max_speed |
Maximum speed (feet per second) for auto-pickup. |
auto_pickup_max_speed = 8.5 |
hoist_payload_station |
Payload station in which the hoist will load in and out of. 1 is first station. |
hoist_payload_station = 4 |
hoist_door |
Door associated with hoist. Must be open for use. |
hoist_door=1 |
[turboshaft_engine]
A turboshaft engine on a helicopter is very similar to a turboprop engine on a fixed wing aircraft.
Property
|
Description
|
Examples
|
power_scalar |
Scalar on Turboprop power. |
power_scalar = 1.0 |
maximum_torque |
Maximum torque available (ft-lbs). |
maximum_torque = 1335 |
powerspecificfuelconsumption |
Brake power specific fuel consumption. |
PowerSpecificFuelConsumption = 0.55 |
Standard Helicopter Sections
[helicopter]
Property
|
Description
|
Examples
|
lift_aero_center |
The longitudinal position, in feet, from the datum of the helicopter that represents the vertical aerodynamic center. |
lift_aero_center = -34.0 |
reference_length |
The length of the helicopter, in feet.
|
reference_length = 21.58 |
reference_frontal_area |
The cross section area of the fuselage, in feet squared, as viewed from head on to the helicopter. |
reference_frontal_area = 17.7 |
reference_side_area |
Total side area of the fuselage, in feet squared, as viewed from directly abeam of the helicopter.
|
reference_side_area = 44.5 |
side_aero_center |
The longitudinal position, in feet, from the datum of the helicopter that represents the lateral aerodynamic center.
|
side_aero_center = -12.5 |
right_trim_scalar |
Scalar on the effect of the trim that counters dissymmetry of lift. The trim normally induces a roll moment to the right, but a negative value will create a left moment.
|
right_trim_scalar = 1.0 |
correlator_available |
This flag determines if a collective/throttle correlator is configured on the helicopter.
|
correlator_available = 1 |
governed_pct_rpm_ref |
Defines the percent rpm that the governor attempts to maintain. 1.0 = 100% of “rated” rpm, although a few percent above that is normal.
|
governed_pct_rpm_ref = 1.04 |
governor_pid |
Proportional – Integral – Derivative (PID) feedback controller that works to maintain the reference rpm. The series of numbers are:
- proportional controller constant
- integral controller constant
- derivative controller constant
- max rpm error (where 1.0 = 100%) in which the integrator portion is active
- max rpm error (where 1.0 = 100%) in which the derivative portion is active
|
governor_pid = 0.4, 0, 0.1, 0, 0.2 |
rotor_brake_scalar |
Scalar on the effect of the rotor brake.
|
rotor_brake_scalar = 1.0 |
torque_scalar |
Scalar on the effect that the rotor has on the yawing moment of the helicopter.
|
torque_scalar = 1.0 |
cyclic_roll_control_scalar |
Scalar on the amount of roll control authority from lateral movement of the cyclic. |
cyclic_roll_control_scalar =1.0 |
cyclic_pitch_control_scalar |
Scalar on the amount of pitch control authority from fore/aft movement of the cyclic. |
cyclic_pitch_control_scalar =1.0 |
pedal_control_scalar |
Scalar on the amount of yaw control authority from movement of the anti-torque pedals. |
pedal_control_scalar =1.0 |
collective_on_rotor_torque_scalar |
Scalar on the amount of torque exerted on the rotor system due to the collective pitch of the rotor blades. Increasing this constant will result in the rotor rpm tending to decelerate more dramatically as collective is increased.
|
collective_on_rotor_torque_scalar = 1.0 |
[fuselage_aerodynamics]
Property
|
Description
|
Examples
|
drag_force_cf |
Coefficient of longitudinal drag. |
drag_force_cf = 0.55 |
side_drag_force_cf |
Coefficient of lateral drag. |
side_drag_force_cf = 10.0 |
pitch_damp_cf |
Pitch damping coefficient (resistance to pitch
velocity). |
pitch_damp_cf = -2.0 |
roll_damp_cf |
Roll damping coefficient (resistance to roll velocity).
|
roll_damp_cf = -2.0 |
yaw_damp_cf |
Yaw damping coefficient (resistance to yaw velocity). |
yaw_damp_cf = -0.1 |
yaw_stability_cf |
Yaw stability coefficient. This is the weathervane
effect. |
yaw_stability_cf = 0.27 |
[mainrotor]
Property
|
Description
|
Examples
|
static_pitch_angle |
When the stick is centered, the pitch angle of the rotor disk, in degrees. |
static_pitch_angle = 2 |
static_bank_angle |
When the stick is centered, the bank angle of the rotor disk, in degrees. |
static_bank_angle = 0 |
position |
Position relative to datum reference point. This
position should be the center of the main rotor. |
Position = -8.5, 0, 4.91 |
radius |
The radius of the rotor, in feet. |
Radius = 12.583 |
max_disc_angle |
The maximum absolute deflection angle up or down, in
degrees, that the rotor disc can move with the cyclic. |
max_disc_angle = 5.0 |
ratedrpm |
The rated rpm value for the main rotor. |
RatedRpm = 510 |
number_of_blades |
The number of blades in the rotor. |
Number_of_blades = 2 |
weight_per_blade |
Approximate weight, in pounds, of each rotor blade. |
Weight_per_blade = 26.0 |
weight_to_moi_factor |
The constant used in calculating the moment of 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. |
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. |
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. |
Position = -67.6, -3.7, 11.6
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. |
TailRotor = 1 |
radius |
The radius of the rotor, in feet. |
Radius = 6.56
Radius = 1.75 |
Model, Sound, Texture and Panel Files
The panel.cfg File
The panel.cfg file is located in an aircraft’s Panel folder,
and defines the characteristics of the aircraft’s cockpit,
including window settings, view settings, and gauges.
The model.cfg File
The model.cfg file is located in an aircraft’s Model folder and specifies which visual models (.mdl files) represent the aircraft exterior and interior. When designing new models, it is required that the model file be separated into the two parts.
[models]
Property
|
Description
|
Examples
|
normal |
External 3D model used under normal circumstances. |
normal=Diamond_DA42
|
interior |
Internal, virtual cockpit, model. |
interior=Diamond_DA42_interior
|
The model.cfg file also contains references to character setups and animations. The following is an example of a model.cfg file.

Property | Description | Examples | pilot_Base | The location of the pilot animation relative to the model.cfg file. Usually the file will be named Anim_Pilot_AircraftName.mdl. | pilot_Base=..\..\..\Characters\animations\Anim_Pilot_PA34.MDL | pilot_Body | The location of the pilot body relative to the model.cfg file. The body is all parts of the pilot which are not flesh, e.g clothing. Usually the file will be named ou_something.mdl. | pilot_Body=..\..\..\Characters\meshes\ou_MC1.mdl | pilot_Head | The location of the pilot head relative to the model.cfg file. The head contains all parts of the pilot which are flesh, usually head and hands. Usually the file will be named hh_something.mdl. | pilot_Head=..\..\..\Characters\meshes\hh_MC1.mdl | capacity | The number of passengers that the aircraft can have. This is not including the pilot. Each passenger (and the pilot) must have a character socket within the aircraft model. The naming scheme for character sockets is 1A, 1B, 1C etc for the first row, 2A, 2B, 2C etc for the next row from front to back in the aircraft. | capacity=5 | passengerXBase | Where X is the index of the passenger (up to the passenger capacity and number of character slots) this is the location of the passenger animation relative to the model.cfg file. Usually named Anim_Loop_Something.mdl. | passenger1Base=..\..\..\Characters\animations\Anim_Loop_Copilot_A.MDL | passengerXBody | Where X is the index of the passenger (up to the passenger capacity and number of character slots) this is the location of the passenger body relative to the model.cfg file. As with the pilot the body of the passenger contains the parts of the passenger which are not flesh. Usually named ou_something.mdl. | passenger1Body=..\..\..\Characters\meshes\ou_FA1.mdl | passengerXHead | Where X is the index of the passenger (up to the passenger capacity and number of character slots) this is the location of the passenger head relative to the model.cfg file. As with the pilot the head of the passenger contains the parts of the passenger which are flesh. Usually named hh_something. | passenger1Head=..\..\..\Characters\meshes\hh_FA1.mdl | passengerXPropY | Where X is the index of the passenger (up to the passenger capacity and number of character slots) and Y is the index of the prop (a passenger can have multiple props) this is the location of a passenger prop relative to the model.cfg file. These are items which do not fit under the umbrella of body/outfit or head/hands. Usually named prop_something.mdl. | passenger1Prop1=..\..\..\Characters\meshes\prop_booklet.MDL passenger1Prop2=..\..\..\Characters\meshes\prop_headset.MDL |
The pilot and passenger MDL locations are optional. If no pilots or passengers are required for the aircraft or would not fit thematically (e.g for an unmanned aircraft) then they can be omitted and no pilots or characters should show in the aircraft. Note that for each pilot or passenger listed in the model.cfg there must be a matching character slot in the aircraft.
The sound.cfg File
The sound.cfg file is located in an aircraft’s Sound folder,
and defines the sounds to use for that aircraft (such as the sound of
the engine at various speeds, the sound of the landing gear going down,
and so on). Refer to the Sound Configuration files document for more
details.
The Texture Folder
An aircraft’s textures are defined by the .bmp files in the
aircraft’s Texture folder, and are projected onto
the aircraft’s parts as
specified in the aircraft’s visual model (.mdl) file, located
in the Model folder. Texture file names must correspond to the texture
files that are referenced in the .mdl file. If the file names don't
correspond, the textures will not be rendered.
Texture files are mipmapped. A mipmapped
texture consists of a sequence of images, each of which is a
progressively lower resolution, prefiltered representation of the same
image. Mipmapping is a computationally low-cost way of improving the
quality of rendered textures. Each prefiltered image, or level, in the
mipmap is a power of two smaller than the previous level. A
high-resolution level is used for objects that are close to the viewer.
Lower-resolution levels are used as the object moves farther away.
To edit a mipmapped texture, you’ll need to use Image Tool,
an image editing application included with the SDK.
Be sure to save a copy of the original file before attempting to
modify it.
A texture can also be edited using a simple graphics application such
as Paint, though it will be saved as a standard .bmp file
instead of a mipmapped .bmp. Flight Sim World will automatically
generate the mipmaps for the texture, although these mipmaps may not
be of as high a quality as mipmaps created using ImageTool.
Notes on using Aliasing
Aliasing allows multiple aircraft, or other objects such as vehicles or boats, to use the same
files
(panels, flight models, sounds, etc.). This saves disk space and makes
file organization more efficient. You can alias an object ’s
panel.cfg, model.cfg, and sound.cfg files from any other
object. Whereas configuration sets allow objects within
a single container to share components, aliasing allows
objects in different containers to share components. To alias a panel.cfg, model.cfg, or sound.cfg
file, simply change the aliasing object's configuration
file to read:
[fltsim]
alias=objectname\panel
or
[fltsim]
alias=objectname\model
or
[fltsim]
alias=objectname\sound
Aliased files are searched for in the following order:
- Relative path from the object type folder (one of: Airplanes, Animals, Boats, GroundVehicles, Misc or Rotorcraft).
- Relative path from the Flight Sim World folder.
An example
Let’s say you’ve imported a Diamond DA42 aircraft
variant into the simulation, but want to use the G1000 panel from the existing Diamond DA42 when flying it. Instead of duplicating all the existing DA42 panel files
(Panel.cfg and .bmps) and putting them in the new DA42 aircraft
container, you can alias to them in their existing location from the
DA42 panel.cfg file. Just change the new DA42 panel.cfg file to read:
[fltsim]
alias=DA42\panel
The new DA42 aircraft would then use the DA42 panel.cfg file
(and the
associated .bmps). The syntax for aliasing model.cfg and sound.cfg
files is identical.

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