flight_model.cfg

The FlightModel.cfg File In The SimObject Editor

 

The flight_model.cfg file is an optional aircraft file for defining the flight model of the aircraft. In general, you'll want to prepare this file using the DevMode tools (see here for more information) and then tweak the values if required in the CFG file.

 

Below you can find information on the different sections used in the flight_model.cfg file as well as what parameters and values are expected within them. You can also find an in-depth explanation of the physics behind the flight model from the following page:

NOTE: To help with the configuration of the Flight Model (and the engines.cfg) we have included an *.xlsx file with the documentation that can be used to generate the required values for many of the parameters based on a small number of inputs (these inputs are marked in blue in the file): PlanePerformance.xlsx

 

 

[Version]

The [Version] section provides version information for the configuration file. In Microsoft Flight Simulator 2024, major versions should always be at least equal to 1.

 

Note that this section information is mandatory and should always be included.

 

Parameter Description Type Required
major Major CFG file version number, values must be greater than 0. Integer Yes
minor Minor CFG file version number, values must be greater than 0. Integer Yes

 

 

[WEIGHT_AND_BALANCE]

This section is used to define the weight and balance of the aircraft. Most position parameters in this section are given relative to the Datum Reference Point for the aircraft, which is itself specified in this section. The convention for positions is that a positive value equals forward, to the right, or vertically upward, and note that all units are in ft, unless mentioned otherwise. Any 3D coordinates are given with respect to this referential in the following order:

  • z (longitudinal) coordinate
  • x (lateral) coordinate
  • y (vertical) coordinate

The only parameters that are not relative to the datum reference are the parameters for the manual longitudinal positioning of the CoL, compute_aero_center and aero_center_lift.

 

The available parameters for this section are:

 

Parameter Description Type Required
max_gross_weight The maximum total weight of the aircraft when fully loaded, in lbs. Float Yes
max_zero_fuel_weight The maximum weight of the aircraft when fully loaded but with empty fuel tanks, in lbs. Defaults to the max_gross_weight value if not supplied. Float No
max_takeoff_weight

The maximum permitted takeoff weight of the aircraft, as defined by the aircraft manufacturer, in lbs.

Defaults to the max_gross_weight value if not supplied.

Float No
max_landing_weight

The maximum permitted landing weight of the aircraft, as defined by the aircraft manufacturer, in lbs.

Defaults first to max_takeoff_weight if a value is not supplied. If that paramater isn't defined then it defaults to the max_gross_weight value.

Float No
empty_weight The empty weight of the aircraft, in lbs. Float Yes
reference_datum_position

The position of the Datum Reference Point relative to the model center. A three value list - z, x, y - with values in ft.

IMPORTANT! The reference datum position should always be defined in the common folder of the modular aircraft, and it should not be changed by presets or attachments. Setting or changing the datum in presets or attachments may cause issues with multiple simulation systems.

List of 3 Floats

Yes
empty_weight_CG_position The position of airplane empty weight CG relative to the Datum Reference Point. A three value list - z, x, y - with values in ft.

List of 3 Floats

Yes
CG_forward_limit

Forward limit of the CG as a Percent Over 100. For example, 0.11 is equal to 11% MAC.

NOTE: This parameter is only valid for airplanes.

Float Yes
CG_aft_limit

Aft limit of the CG as a Percent Over 100. For example, 0.4 is equal to 40% MAC.

NOTE: This parameter is only valid for airplanes.

Float Yes
CG_feet_forward_limit

The forward limit (longitudinal offset) of the CG expressed in ft from the Datum Reference Point.

NOTE: This parameter is only valid for helicopters.

Float Yes
CG_feet_aft_limit

The aft limit (longitudinal offset) of the CG expressed in ft from the Datum Reference Point.

NOTE: This parameter is only valid for helicopters.

Float Yes
CG_feet_lateral_right_limit

The right-side (lateral offset) limit of the CG expressed in ft from the Datum Reference Point.

NOTE: This parameter is only valid for helicopters.

Float Yes
CG_feet_lateral_left_limit

The left-side (lateral offset) limit of the CG expressed in ft from the Datum Reference Point.

NOTE: This parameter is only valid for helicopters.

Float Yes
empty_weight_pitch_MOI The empty pitch MOI, in Slug sqft. Float Yes
empty_weight_roll_MOI The empty roll MOI, in Slug sqft. Float Yes
empty_weight_yaw_MOI The empty yaw MOI, in Slug sqft. Float Yes
empty_weight_coupled_MOI The empty transverse MOI, in Slug sqft. Float Yes
activate_mach_limit_based_on_cg

When set to TRUE (1) this activates mach limitation depending on CG position.

Default for most aircraft is FALSE (0).

Bool Yes
activate_cg_limit_based_on_mach

When set to TRUE (1) this activate CG limitation depending on the mach value.

Default for most aircraft is FALSE (0).

Bool Yes
max_number_of_stations The maximum number of payload stations. Integer Yes
station_load.N

This parameter can be used multiple times to define each of the payload stations up to the maximum defined by the max_number_of_stations value (note that counting starts at 0, so for 15 stations N would be from 0 to 14). Parameter takes a comma separated list with the following format:

weight, x, y, z, name, type

The weight is in lbs, (x, y, z) is the offset from the Datum Reference Point and in ft, and the name is a localisable string.

Note that for legacy aircraft, there is an additional parmeter, type:

weight, x, y, z, name, type

The type can be one of the following integer values:

  1. - 0 (Unknown)
  2. - 1 (Pilot)
  3. - 2 (Copilot)
  4. - 3 (Passenger)
  5. - 4 (Front Passengers)
  6. - 5 (Rear Passengers)
  7. - 6 (Baggage)

List of 6 Values

No
(Unless max_number_of_stations is greater than 0)
station_name.N

This parameter defines a name that will be used in the payload dialog, and has a 15 character limit. Omission of this will result in a generic station name being used. This parameter can be used multiple times to define names for each of the payload stations up to the maximum defined by the max_number_of_stations value (note that counting starts at 0, so for 15 stations N would be from 0 to 14).

String No
(Unless max_number_of_stations is greater than 0)

 

 

[CONTACT_POINTS]

This section is for defining the points on the aircraft body referential frame which are likely to come in contact with the ground. These parameters are used for aircraft positioning on the ground and also for crash simulations. Contact points should be added through the SimObject Editor, and only tweaked if required through the flight_model.cfg file.

 

This section has the following parameters:

 

Parameter Description Type Required
static_pitch

The pitch when at rest on the ground, in degrees, where a positive value is "up" and a negative value is "down".

IMPORTANT: Static pitch is only used when the physics simulation for the aircraft is not active: for example in the Hangar or in ready-to-take-off RTCs.

Float Yes
static_cg_height

The altitude of the CG when at rest on the ground, in ft.

IMPORTANT: Static CG height is only used when the physics simulation for the aircraft is not active: for example in the Hangar or in ready-to-take-off RTCs.

Float
tailwheel_lock Sets whether the tailwheel lock is available (TRUE, 1) or not (FALSE, 0). Bool
gear_system_type Sets the gear system type for the aircraft.

Integer:

  1. 0 = electrical
  2. 1 = hydraulic
  3. 2 = pneumatic
  4. 3 = manual
  5. 4 = none
  6. 5 = undefined
emergency_extension_type Sets the type of emergency extension system that can be used.

Integer:

  1. 0 = None
  2. 1 = Pump
  3. 2 = Gravity
  4. 3 = Hydraulic backup reserve (Needs [HYDRAULIC_SYSTEM])
gear_locked_on_ground Defines whether or not the landing gear handle is locked to down when the plane is on the ground (TRUE, 1) or not (FALSE, 0). Bool
gear_locked_above_speed Defines the speed at which the landing gear handle becomes locked in the up position, in ft per second. Note that a value of -1 can be used to disable this option. Float
locked_tailwheel_max_range

This defines the maximum angle of the tailwheel when locked, in radians. Default is 0.

Float
allow_stopped_steering This can be used to enable (TRUE, 1) steering when the aircraft is stopped or not (FALSE, 0). Bool
max_speed_full_steering Defines the speed under which the full angle of steering is available, in ft per second. Float
max_speed_decreasing_steering Defines the speed above which the angle of steering stops decreasing, in ft per second. Float
min_available_steering_angle_pct Defines the percentage of steering which will always be available even above max_speed_decreasing_steering, in Percent Over 100 Float
max_speed_full_steering_castering Defines the speed under which the full angle of steering is available for free castering wheels, in ft per second. Float
max_speed_decreasing_steering_castering Defines the speed above which the angle of steering stops decreasing for free castering wheels, in ft per second. Float
min_castering_angle Defines the minimum angle a free castering wheel can take (in radians). Float
max_castering_angle Defines the maximum angle a free castering wheel can take (in radians). Float
hyd_need_power_to_function

Sets whether the hydraulic systems for the landing gear require power to function (1, TRUE) or not (0, FALSE). Default value is 1, TRUE.

NOTE: This parameter is only taken into consideration when the gear_system_type parameter is set to 1 (hydraulic).

Bool
set_max_compression

This can be used to change the way how the 10th parameter in the point.N list will be used. If set to 1 (true) then the 10th parameter specifies the maximum compression of contact points (in feet) instead of their maximum-to-static compression ratio (which is by default, unitless).

Default value is 0 (false).

Boolean No
spring_exponential_fix

This parameter is only required to fix a potential issue related to the 17th parameter in the point.N definition, "Exponential Constant". When this exponential constant is greater than 1, or very close to 1, the default algorithm lowers the spring force if compression is low. When this is set to 1 (TRUE), if the exponential constant is greater than 1 then it becomes the denominator for the linear spring force curve in the low compression range, and the power of this curve in the high compression range. For more information, see Notes On The Exponential Constant below.

Default value is 0 (FALSE).

Bool No
water_longitudinal_friction_scalar

This parameter is a scalar used to modify the water friction for all contact points on the Z axis.

Default value is 1.

Float No
water_lateral_friction_scalar

This parameter is a scalar used to modify the water friction for all contact points on the X axis.

Default value is 1.

Float No
water_steering_friction_scalar

This parameter is a scalar used to modify the water friction on the X axis for water rudders.

Default value is 1.

Float No
point.N Hashmap used to give the contact point a name and properties. This parameter can be used multiple times to define each of the contact points (note that counting starts at 0, so for 5 points N would be from 0 to 4). For the actual keys and values required, please see below.

Hash Map

No
(Unless max_number_of_points is greater than 0)

 

 

point.N

The point parameter is a hash map with the following keys:

 

Key Value Description Required
Name String This is a name string that is used as an alias to identify the contact point. It will also be used as the reference index for SimVars, and note that the name is the only guaranteed reference to the component due to the fact that the Modular Aircraft Merging process may change the index. The name cannot contain special characters or spaces. Yes
Properties List

Table that contains all the information about the interactive point.

Yes

 

The Properties key is a list of 18 values, as shown in the following example:

point.0 = Name: wheel1 #Properties: 1, -13, 0, -0.65, 750, 0, 0.523, 90, 0.296, 2.5, 0.794, 0, 0, 0, 165, 165, 1, 1

 

Each of these property values is for a specific piece of information about the contact point, which we list in the table below for reference:

 

List Position Description Type Required
0

This sets the type of contact point being defined. Please refer to the following notes for additional information that will be important depending on the type contact point being defined:

  1. Notes On Skids
  2. Notes On Tailwheels
  3. Notes On Floats
  4. Note On Collision Damage / Wear And Tear (for scrape points)
  5. Note On Ground Contact Model

Integer:

  1. 1 = wheel
  2. 2 = scrape points
  3. 3 = skids
  4. 4 = float
  5. 5 = water rudder
  6. 16 = ski
  7. 17 = propeller
  8. 18 = liquid dropping system scoop
Yes
1 Longitudinal position z relative to Datum Reference Point, in ft. Float Yes
2 Lateral position x relative to Datum Reference Point, in ft. Float Yes
3 Vertical position y relative to Datum Reference Point, in ft. Float Yes
4 Impact damage threshold crash velocity, in ft per minute. Float Yes
5 The brake type the wheel contact uses.

Integer:

  1. 1 = brake on left gear
  2. 2 = brake on right gear
  3. 3 = brake on both gears
Yes if the position 0 contact value is 1 (for a wheel).
6 The wheel radius, in ft. Float Yes if the position 0 contact value is 1 (for a wheel).
7 Wheel max steering angle, in degrees, between -90 and 90. Float Yes if the position 0 contact value is 1 (for a wheel).
8

The static compression coefficient constant (which is used to compute spring reaction when on the ground), in ft. If the contact point is rigid, then set this to 0.

Please see Notes On Spring/Damping Factors for more information.

Float Yes
9

If the set_max_compression parameter is set to 1 (true) then this specifies the maximum compression of the contact point, in feet. If the parameter is set to 0 (false) then this sets the maximum-to-static compression ratio for the contact point (a unitless value).

Please see Notes On Spring/Damping Factors for more information.

Float No
10

The damping ratio constant (used to compute ground reaction damping). A value between 0.0 (un-damped) and 1.0 (critically damped)

Please see Notes On Spring/Damping Factors for more information.

Float Yes
11 Extension time, in seconds. This is the time required to fully extend wheels/water rudder/skis/floats. Float Yes
12 Retraction time, in seconds. This is the time required to fully retract wheels/water rudder/skis/floats. Float Yes
13 Identifies the type of sound that is going to be played for the contact point.

Integer:

  1. 0 = Center Gear
  2. 1 = Auxiliary Gear
  3. 2 = Left Gear
  4. 3 = Right Gear
  5. 4 = Fuselage Scrape
  6. 5 = Left Wing Scrape
  7. 6 = Right Wing Scrape
  8. 7 = Aux1 Scrape
  9. 8 = Aux2 Scrape
  10. 9 = Tail Scrape
Yes
14 The airspeed limit for gears retraction, in kias. Float No
15

Airspeed above which gear is damaged, in kias.

For more information see here: Landing Gear Damage.

Float No
16 The exponential constant for springs (if in doubt, omit or set to 1). For more information, see Notes On The Exponential Constant. Float No
17

The extension mode to use for landing gear. This parameter defines how an extendable contact point should react to the gear handle moving, which can be one of the following values:

  • 0: manual - the gear goal will not follow the gear handle position (meaning that the "goal" position when extending/retracting the landing gear can be set from an external source)
  • 1: automatic - the gear goal will follow the gear handle position

If omitted then the default behaviour will be automatic (1).

Bool No

 

 

[COLLISION_DAMAGE]

This section is for defining the points on the aircraft body referential frame which are likely to come in contact with the ground. These parameters are used for aircraft positioning on the ground and also for crash simulations. Contact points should be added through the SimObject Editor, and only tweaked if required through the flight_model.cfg file. You can find additional information on how the wear and tear and collision damage parameters work from the following section:

 

This section has the following parameters:

 

Parameter Description Type Required
CollisionDamage.N

This parameter is used to set up a collision "profile" which can be used elsewhere. This profile is comprised of the following key/value pairs:

  • Name: The name of the profile
  • Contact Point: The name of the contact point to associate the profile with (must be of the type scrape point).
  • Factor: The factor to multiply the damage from the contact point with.

For example:

CollisionDamage.0 = Name:LeftWingLightDamage # ContactPoint:Wing_Left # Factor:0.1

 

Once you have this profile, you can assign it to various parts (as listed here) and if the contact point is involved in a collision, then damage will be propagated to the parts that reference the profile based on the factor used in the profile. A factor of 1 means that 100% of the damage will be propagated, and 0 means no damage will be propagated.

Hash Map

No
AileronLeft

This is used to assign one or more damage profiles to the left aileron. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the aileron.

For example:

AileronLeft = WearAndTearCollision : LeftWingLightDamage, LeftWingHeavyDamage

Hash Map

No
AileronLeftCable

This is used to assign one or more damage profiles to the left aileron control cable. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the aileron control cable.

For example:

AileronLeftCable = WearAndTearCollision : LeftWingLightDamage, LeftWingHeavyDamage

Hash Map

No
AileronRight

This is used to assign one or more damage profiles to the right aileron. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the aileron.

For example:

AileronRight = WearAndTearCollision : RightWingLightDamage, RightWingHeavyDamage

Hash Map

No
AileronRightCable

This is used to assign one or more damage profiles to the right aileron control cable. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the aileron control cable.

For example:

AileronLeft = WearAndTearCollision : RightWingLightDamage, RightWingHeavyDamage

Hash Map

No
Rudder

This is used to assign one or more damage profiles to the rudder. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the rudder.

For example:

Rudder = WearAndTearCollision : LeftWingLightDamage, RightWingLightDamage

Hash Map

No
RudderCable

This is used to assign one or more damage profiles to the rudder control cable. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the rudder control cable.

For example:

RudderCable = WearAndTearCollision : LeftWingLightDamage, RightWingLightDamage

Hash Map

No
Elevator

This is used to assign one or more damage profiles to the elevator. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the elevator.

For example:

Elevator = WearAndTearCollision : LeftWingLightDamage, RightWingLightDamage

Hash Map

No
ElevatorCable

This is used to assign one or more damage profiles to the elevator control cable. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the elevator control cable.

For example:

ElevatorCable = WearAndTearCollision : LeftWingLightDamage, RightWingLightDamage

Hash Map

No
FlapsLeft

This is used to assign one or more damage profiles to the left flaps. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the left flaps.

For example:

FlapsLeft = WearAndTearCollision : LeftWingLightDamage, LeftWingHeavyDamage

Hash Map

No
FlapsLeftCable

This is used to assign one or more damage profiles to the left flaps control cable. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the left flaps control cable.

For example:

FlapsLeftCable = WearAndTearCollision : LeftWingLightDamage, RightWingLightDamage

Hash Map

No
FlapsRight

This is used to assign one or more damage profiles to the right flaps. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the right flaps.

For example:

FlapsRight = WearAndTearCollision : RightWingLightDamage, RightWingHeavyDamage

Hash Map

No
FlapsRightCable

This is used to assign one or more damage profiles to the right flaps control cable. The information is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter, to associate with the flaps control cable.

For example:

FlapsRightCable = WearAndTearCollision : LeftWingLightDamage, RightWingLightDamage

Hash Map

No
LandingGear.N

This parameter permits you to assign a damage profile to one or more landing gear. The parameter is indexed from 1, and indices must be consecutive. Indices refer to a contact point of the type wheel where index 1 is the first one defined in the contact point section, regardless of it's position in the contact point list. Index 2 wll be the second defined wheel, 3 the third, etc...

 

The information for each landing gear is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter.

For example:

LandingGear.1 = WearAndTearCollision:LeftWingLightDamage
LandingGear.2 = WearAndTearCollision:RightWingLightDamage

 

Hash Map

No
Engine.N

This parameter permits you to assign a damage profile to one or more engines. The parameter is indexed from 1, and indices must be consecutive. Indices refer to the engine the profile should be applied to, counting from left to right.

 

The information for each engine is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter.

For example:

Engine.1 = WearAndTearCollision:LeftLightDamage
Engine.2 = WearAndTearCollision:RightLightDamage

Hash Map

No
EngineOilTank.N

This parameter permits you to assign a damage profile to one or more engine oil tank. The parameter is indexed from 1, and indices must be consecutive. Indices refer to the engine the profile should be applied to.

 

The information for each oil tank is given as a hash map with the following key:

  • WearAndTearCollision: A list of damage profile names, as defined in the CollisionDamage.N parameter.

For example:

EngineOilTank.1 = WearAndTearCollision:LeftLightDamage
EngineOilTank.2 = WearAndTearCollision:RightLightDamage

Hash Map

No

 

 

[FUEL]

This section is for defining a simplified fuel system that will reflect on the flight model. In general this section is where you'd define fuel systems for basic aircraft, but for more complex aircraft you have the [FUEL_SYSTEM] section which permits you to setup how fuel will be distributed and used within the aircraft on a much more detailed level.

 

This section has the following parameters:

 

Parameter Description Type Required
LeftMain

Comma separated list of values that defines the tank. List values are:

z, x, y, total_fuel_capacity, unusable_fuel_capacity

(z, x, y) is offset from the Datum Reference Point and in ft, and the fuel capacity values are in Gallons. If any tank is not used, simply supply the list with all values set to 0.

List of 5 Values

Yes
RightMain
Center1
Center2
Center3
LeftAux
LeftTip
RightAux
RightTip
External1
External2
fuel_type

The fuel type for the engines.

Integer:

  1. 1 = OCTANE 100
  2. 2 = JET A
  3. 3 = OCTANE 80
  4. 4 = AUTO GAS
  5. 5 = JET B
Yes
number_of_tank_selectors The number of tank selectors available, between 1 and 4 only. Integer Yes
electric_pump Whether there is an electric pump (TRUE, 1) or not (FALSE, 0). Bool No
engine_driven_pump Whether there is an engine driven pump (TRUE, 1) or not (FALSE, 0). Bool No
manual_transfer_pump Whether there is a manual transfer pump (TRUE, 1) or not (FALSE, 0). Bool No
manual_pump Whether there is a manual pump (TRUE, 1) or not (FALSE, 0). Bool No
anemometer_pump Whether there is an anemometer pump (TRUE, 1) or not (FALSE, 0). Bool No
fuel_dump_rate The fuel dump rate, as a Percent Over 100. Float No
max_pressure_auto_pump The maximum pressure for the auto pump, in psi. Float No
fuel_transfer_pump.N

Defines a fuel transfer pump N, where N starts at 0. Table contents are:

Source, Destination, Rate in lbs/s, Pump ID

Source and Destination are one of the values given here for the different tanks: Fuel Tank Selection. The Pump ID is an integer value used to identify the pump and link it to a circuit.

To toggle the pump on or off you need to have first created a circuit of the type CIRCUIT_FUEL_TRANSFER_PUMP using the circuit.N parameter of the systems.cfg file, and the circuit Type index needs to be the same as the Pump ID.

The pump can then be toggled on/off using the FUEL_TRANSFER_CUSTOM_INDEX_TOGGLE key event, or using the ELECTRICAL_CIRCUIT_TOGGLE key event.

List of 4 Values

No
default_fuel_tank_selector The default fuel selector used in case of autostart, which will override default_fuel_tank_selector.N.

Integer:

  1. 0 = Off
  2. 1 = All
  3. 2 = Left
  4. 3 = Right
  5. 4 = Left Aux.
  6. 5 = Right Aux.
  7. 6 = Center 1
  8. 7 = Center 2
  9. 8 = Center 3
  10. 9 = External 1
  11. 10 = External 2
  12. 11 = Right Tip
  13. 12 = Left Tip
  14. 13 = Crossfeed
  15. 14 = Crossfeed

    Left-to-Right
  16. 15 = Crossfeed

    Right-to-Left
  17. 16 = Both
  18. 17 = All External
  19. 18 = Isolate
  20. 19 = Left Main
  21. 20 = Right Main
No
default_fuel_tank_selector.N Default fuel selector used in case of autostart for engine N, where N corresponds to an engine (between 1 and 4). This will be ignored if default_fuel_tank_selector is defined. Yes
fuel_tank_priority

This is a table of fuel tanks to indicate the order in which they should be used. You list the highest priority first, and then subsequent priorities, for example:

fuel_tank_priority = LeftMain-RightMain, Center1

As you can see, dashes can be used to indicate 2 (or more) fuel tanks sharing the same priority, and in this example both the left and right main tanks are priority 1, then Center1 is priority 2. The following strings can be used to indicate the fuel tanks you want to assign a priority to:

  1. Center1
  2. Center2
  3. Center3
  4. LeftMain
  5. LeftTip
  6. LeftAux
  7. RightMain
  8. RightTip
  9. RightAux
  10. External1
  11. External2

List of Values

No

 

 

[FUEL_SYSTEM]

This section is for defining the aircraft's fuel system in detail. In general, the fuel system should be set up through the SimObject Editor, and only tweaked if required through the flight_model.cfg file using the parameters on this page.

 

The [FUEL_SYSTEM] section is primarily for use in complex aircraft models where the simple [FUEL] system doesn't give enough control or flexibility for the aircraft systems. The parameters within the [FUEL] section should be used for simple aircraft or those that require a basic fuel system setup, or for maintaining old aircraft (like ones imported from FSX).

 

This section only has a few parameters, but each parameter can be repeated a number of times if required, where N in the parameter name corresponds to a new item of that parameter type. For example, the Engine parameter can go from Engine.1 to Engine.4 and each one can be defined separately.

 

The available fuel system parameters are:

 

Parameter Description Type Required
Version

This value corresponds to the various versions of the modern fuel system and is used to permit you to maintain compatibility with already published aircraft as the modern fuel system evolves. The following values are currently accepted:

 

  1. 1: uses the Fuel System as released in Microsoft Flight Simulator 2020 SimUpdate 8 - this was the initial release of the new fuel system and had a bug where (under some conditions) an aircraft would have "infinite" fuel.
  2. 2: uses the Fuel System as updated in Microsoft Flight Simulator 2020 SimUpdate 9 - this update fixed the infinite fuel bug, but had an issue with reduced fuel flow through junctions (under some conditions).
  3. 3: uses the Fuel System as updated in Microsoft Flight Simulator 2020 SimUpdate 10 - this update fixed the reduced fuel flow through junctions bug, however it had an issue loading and saving of junction settings inside of FLT files (sometimes it would save the wrong value which meant you would be on the wrong option when loading the file).
  4. 4: uses the Fuel System as updated in Microsoft Flight Simulator 2020 SimUpdate 11 - this update fixed the issue loading and saving junction setting inside of FLT files.
  5. 5: uses the Fuel System as updated in Microsoft Flight Simulator 2020 SimUpdate 14 - this update fixed the issue loading and saving junction setting inside of FLT files.
  6. Latest: Using this value means that the aircraft will always use the latest available version of the fuel system (currently the initially updated Microsoft Flight Simulator 2024 version). Note that using this option is potentially problematic when publishing an aircraft to the Marketplace, as it may mean that a future SimUpdate could break how the fuel system works.
String Yes
fuel_type

Sets the fuel type to be used by the engine or burner. This can be one of the following:

  1. 0 - NONE
  2. 1 - OCTANE 100
  3. 2 - JET_A
  4. 3 - OCTANE 80
  5. 4 - AUTO GAS
  6. 5 - JET B
  7. 6 - LIQUID PROPANE
Integer Yes
Burner.N

Defines one or more burners (up to a maximum of 16) that form a part of the fuel system. Details on the burner map contents are given here: Burner.N

Note that burners require that the fuel_type be set to 6 (Liquid Propane).

Hash Map

No
APU.N

This defines an APU for the fuel system. You can have multiple APU's per system, numbered from 1 upwards. Details on the APU map contents are given here: APU.N

Engine.N

Defines one or more engines (up to a maximum of 16) that form a part of the fuel system. Details on the engine map contents are given here: Engine.N

Tank.N

Defines one or more fuel tanks that form a part of the fuel system. Details on the tank map contents are given here: Tank.N

Line.N

Defines one or more lines that form a part of the fuel system. Details on the line map contents are given here: Line.N

Junction.N

Defines one or more junctions that form a part of the fuel system. Details on the junction map contents are given here: Junction.N

Valve.N

Defines one or more valves that form a part of the fuel system. Details on the valve map contents are given here: Valve.N

Pump.N

Defines one or more fuel pumps that form a part of the fuel system. Details on the pump map contents are given here: Pump.N

Trigger.N Defines one or more triggers that will be used to change components within the fuel system based on certain conditions. Details on the trigger map contents are given here: Trigger.N
Curve.N A list of values. You can define multiple curves for a fuel system, starting at N = 1, and the curves may be used in multiple different parameters. Details on the list contents are given here: Curve.N

List of Values

No

NOTE: For all parameters, the "Title" key is localisable, but it is also optional and can be omitted in most cases. Currently only the Tank.N title is visible in the Microsoft Flight Simulator 2024 UI.

 

 

[AIRPLANE_GEOMETRY]

This section is for defining the geometry of an aircraft, which is an important part of the Microsoft Flight Simulator 2024 engine, since the flying physics will use, in a large part, the aircraft geometry to simulate the interaction between the SimObject and the physical world. In general, the geometry of the aircraft should be created and edited through the SimObject Editor, and only tweaked if required through the flight_model.cfg file.

NOTE: This section is not required if you are creating a Helicopter SimObject.

 

Note that you can find further information on the physics behind this section from the following page:

 

You can also find a helpful tutorial on the basics of setting up the aircraft geometry from the following page:

 

The available parameters for the [AIRPLANE_GEOMETRY] section are:

 

Parameter Description Type Required
wing_area

Total area of the top surface of the wing from tip-to-tip, in sqft. The wing area impacts the target lift and drag forces. For example it directly impacts lift proportionally to the area:

\(L = 0.5 \times p \times v \times v \times WingArea \times C_L\)

Float Yes
wing_span

The horizontal distance between the two wing tips, in ft. The wing span impacts the distribution of the forces over the aircraft, and the larger the wing span the greater the increase in the roll and yaw moment of ailerons and also the resistance to the roll movement of the aircraft.

Float Yes
wing_root_chord

Length of the wing Chord at the intersection of the wing and the fuselage, in ft. The chord over the wing will be automatically computed based on the area, the span and the chord at the root. To get a rectangle shaped wing, enter the average chord into the root chord. To get a triangle shaped wing enter a root chord larger than the average chord.

Float Yes
wing_camber The wing Camber, in degrees. Wing camber here means the difference in virtual incidence or slope between the back region of the wing and the front region of the wing. A wing with a lot of camber has a big curve while a wing with less camber is more streamlined. Wing camber mostly has an impact on the pitch moment generated at various wing incidences as well as on the position of the aerodynamic center. Float Yes
wing_thickness_ratio

The wing local thickness, calculated as:

\({\textrm{local\_chord}} (x) \times \textrm{wing\_thickness\_ratio}\)

where \(x = \textrm{lateral coord}\)

Value is in ft.

Float Yes
wing_dihedral

This is the angle between the wing leading edge and a horizontal line parallel to the ground, as seen when looking at the front of an aircraft. Technically defined as the dihedral angle Lambda, in degrees. The wing dihedral impacts secondary effects such as induced roll and adverse yaw.

Float Yes
wing_virtualdihedral

Sets the "virtual" dihedral. This values is added to the actual dihedral value, but without moving the surface, proportional to the vertical position of the wing. Note that high wings have more positive virtual dihedral, and low wings have more negative virtual dihedral. You can use this parameter to simulate the pressure build up between wing and fuselage when side slipping.

Default value is 5.0.

Float No
wing_incidence

This is the angle (in degrees) the mean wing Chord makes with a horizontal line parallel to the ground, as seen when looking at the side of an aircraft from the wing tip.

This base wing incidence is calculated when the aircraft surfaces are initially "built" in the simulation and before the normalization of the lift table. The base incidence impacts the zero AoA lift and should be set as closely as possible to the real wing incidence so that the normalization has as little work to do in order to reach the target lift polar. The normalization will readjust this incidence in order to match the target lift coefficient.

Float Yes
wing_twist

This is the difference in wing incidence from the root Chord and the tip Chord of the wing (in degrees). Technically defined as the wing twist epsilon.

Most aircraft have twisted wings in order to increase aileron authority close to and during a stall. This also causes higher incidences towards the root of the wing and will cause these regions to stall earlier, which will cause more symmetrical stalls.

Float Yes
oswald_efficiency_factor

The wing Oswald Efficiency Factor (non dimensional) measures the aerodynamic efficiency of the wing, where a theoretically perfect wing will have a factor of 1.0.

This is the "e" in:

\(C_{Di} = \frac {(C_L)^2} {pi \times AR \times e}\)

While the aspect ratio is defined by the geometry, this factor impacts the induced drag, and most planes have an oswald factor in the order of 0.7.

Float Yes
wing_winglets_flag

Sets whether the aircraft has winglets (TRUE, 1) or not (FALSE, 0). This parameter is not directly used to define the aircraft geometry, however if the aircraft goes through the normalization process that normalizes the performance to the desired drag, then that drag value will include the winglet drag if it is enabled using this parameter.

Bool Yes
wing_sweep

The angle of the wing with the lateral axis. This is the angle the leading edge of the wing makes with a horizontal line perpendicular to the fuselage, as seen when looking down on top of an aircraft (expressed in degrees).

Wing sweep has an important impact on secondary effects but also on the location of the wing on the longitudinal axis. The wing will be positioned to align the default 25% aerodynamic center with the aero_center_lift value and a swept wing will have the root in front of the aerodynamic center while the tip will be in the back. The wing will be automatically skewed to align with the target aerodynamic center position.

Float Yes
wing_pos_apex_vert

Vertical (y) distance of the wing apex - as measured at the centerline of the aircraft - from the Datum Reference Point in ft. This distance is measured positive in the "up" direction.

Float Yes
wing_mindragincidence

This sets the aircraft AoA at which the wing's parasitic drag is minimal (lift induced drag is always minimal when lift is minimal).

Default value is 0.

Float No
htail_area

Area of the static part of the horizontal stabilizer (not counting the elevator area), in sqft. The horizontal stabilizer and elevator will be simulated as a single wing with surfaces positioned in a way that the overall incidence matches the current control surface deflection. This single surface will have the area of htail_area and elevator_area combined. However, we recommend entering the exact area of each surface. This area will impact the pitch moment caused by the elevator deflection as well as the pitch moment caused by the horizontal stabilizer.

Float Yes
htail_span

The horizontal span of the htail and elevator surface, in ft. A large htail span will impact the roll moment of the propeller wash but also resist the aircraft roll movement.

Float Yes
htail_pos_lon

Longitudinal (z) distance of the horizontal tail apex and elevator surface - as measured at the centerline of the aircraft - from the Datum Reference Point in ft. This distance is measured positive in the forward (aircraft nose) direction.

The longitudinal position of the htail impacts the pitch moment of the htail and elevator surfaces. The htail force vectors should be aligned with the real surface.

Float Yes
htail_pos_vert

Vertical (y) distance of the horizontal tail apex and elevator surface - as measured at the centerline of the aircraft - from the Datum Reference Point in ft. This distance is measured positive in the "up" direction.

Depending on the vertical position of the htail, it can get into turbulences created by the wing located in front of it. In extreme situations this can create a deep and unrecoverable stall.

Float Yes
htail_incidence

The default incidence of the htail and elevator surface combination. This is the angle the mean horizontal tail Chord makes with a horizontal line parallel to the ground, as seen when looking at the side of an aircraft from the horizontal tail tip (in degrees).

The aircraft surfaces will be build with this default incidence setting and all performance normalization will be calculated with this incidence. This means that the target lift and drag coefficients will match the aircraft with this htail_incidence default elevator angle. Any other elevator angle will generate different drag and lift coefficients.

We recommend setting the htail_incidence so that the aircraft flies level at cruise speed without any required elevator input and zero elevator trim. This means that the htail_incidence will be the neutral trim for cruise speed. By doing this the lift and drag coefficients of the aircraft will perfectly match the target values during cruise and the drag force will be the most accurate and match the target performance during cruise. This also means that during any other phase, the drag performance of the aircraft won't perfectly match the target formula because of the added drag caused by the added elevator deflection required to maintain a level flight at any other speed. This target formula is expressed as:

\({C_D} = {C_{D0}} + K(C_L - C_{L0})^{2}\)

However, it is possible to chose a different speed than cruise and set the htail_incidence for that speed.

Float Yes
htail_sweep This is the angle the horizontal tail leading edge makes with a horizontal line perpendicular to the fuselage, as seen when looking down on top of an aircraft (in degrees). Float Yes
htail_thickness_ratio

The horizontal tail local thickness, calculated as:

\({\textrm{local\_chord}} (x) \times \textrm{htail\_thickness\_ratio}\)

where \(x = \textrm{lateral coord}\)

Value is in ft.

Float Yes
vtail_area

The fuselage-to-tip area of the static part of the vertical stabilizer (not counting the rudder area), in sqft. The vertical stabilizer and rudder will be simulated as a single wing with surfaces positioned in a way such that the overall incidence matches the current control surface deflection. This single surface will have the area of vtail_area and rudder_area combined. However, we recommend entering the exact area of each surface. This area will impact the yaw moment caused by the rudder deflection as well as the yaw moment caused by the vertical stabilizer.

Float Yes
vtail_span

The vertical tail span is the vertical distance from the vertical tail-fuselage intersection to the tip of the vertical tail, in ft.

A large vtail span will impact the roll moment of the propeller wash but also resist the aircraft roll movement. It will also counter adverse yaw and counter induced roll during rudder inputs.

Float Yes
vtail_sweep This is the angle the vertical tail leading edge makes with a vertical line perpendicular to the fuselage, as seen when looking at the side of the vertical tail (in degrees). Float Yes
vtail_pos_lon

Longitudinal (z) position of the vtail and rudder surface - as measured at the centerline of the aircraft - from the Datum Reference Point in ft. This distance is measured positive in the forward (aircraft nose) direction.

The longitudinal position of the vtail impacts the yaw moment of the vtail and rudder surfaces. The vtail force vectors should be aligned with the real surface.

Float Yes
vtail_pos_vert

Vertical position of the vtail and rudder surface - as measured at the centerline of the aircraft - from the Datum Reference Point in ft. This distance is measured positive in the "up" direction.

Depending on the vertical position of the vtail, it can get into turbulences created by the wing located in front of it. The vertical position of the vtail will impact the roll moment created by the surface.

Float Yes
vtail_thickness_ratio

The vertical tail local thickness, calculated as:

\({\textrm{local\_chord}} (x) \times \textrm{vtail\_thickness\_ratio}\)

where \(x = \textrm{lateral coord}\)

Value is in ft.

Float Yes
fuselage_length The fuselage length from nose to tail, in ft. Float Yes
fuselage_diameter

The approximate fuselage diameter, in ft. This value is used to limit the the drone camera and for other things like POI notification placement, etc...

If this parameter is not included in the file, then the diameter will be inferred from the wing mean chord length and other data.

Float No
fuselage_center_pos The fuselage center from the Datum Reference Point, in ft.

List of 3 Floats

Yes
fuselage_mindragincidence Aircraft AoA at which the fuselage's drag is minimal.
Default value is 0.
Float No
cockpit_width

The approximate width of the cockpit area, in ft.

If you include this parameter then you should also include the cockpit_height parameter. If neither are used, then the width/height will be inferred from the fuselage_diameter.

Float No
cockpit_height

The approximate height of the cockpit area, in ft.

If you include this parameter then you should also include the cockpit_width parameter. If neither are used, then the width/height will be inferred from the fuselage_diameter.

Float No
elevator_area

Area of the moving part of the horizontal stabilizer (not counting the htail area), in sqft.

The horizontal stabilizer and elevator will be simulated as a single wing with surfaces positioned in a way that the overall incidence matches the current control surface deflection. This single surface will have the area of htail_area and elevator_area combined. However, we recommend entering the exact area of each surface. This area will impact the pitch moment caused by the elevator deflection as well as the pitch moment caused by the horizontal stabilizer.

Float Yes
aileron_area The top surface aileron area, in sqft. Float Yes
aileron_to_elevator_gain

Scales the elevator deflection angle in relation to the aileron deflection angle.

Default value is 0.

Float No
rudder_area

Area of the moving part of the vertical stabilizer (not counting the vtail area),in sqft.

The vertical stabilizer and rudder will be simulated as a single wing with surfaces positioned in a way that the overall incidence matches the current control surface deflection. This single surface will have the area of vtail_area and rudder_area combined. However, we recommend entering the exact area of each surface. This area will impact the yaw moment caused by the rudder deflection as well as the yaw moment caused by the vertical stabilizer.

Float Yes
elevator_up_limit

Upper angular limit of the elevator and htail combined control surface, in degrees.

This should be the maximum elevator deflection angle possible and will be scaled down by the elasticity table and the elevator_maxangle_scalar.

Float Yes
elevator_down_limit

Lower angular limit of the elevator and htail combined control surface, in degrees (absolute values only).

This should be the maximum elevator deflection angle possible and will be scaled down by the elasticity table and the elevator_maxangle_scalar.

Float Yes
aileron_up_limit

Upper angular limit of the aileron and wing combined control surface, in degrees.

This should be the maximum aileron deflection angle possible and will be scaled down by the elasticity table and the aileron_effectiveness.

Float Yes
aileron_down_limit

Lower angular limit of the aileron and wing combined control surface, in degrees (absolute values only).

This should be the maximum aileron deflection angle possible and will be scaled down by the elasticity table and the aileron_effectiveness. An excessive aileron down limit may increase the chance of the related wing surface stalling.

Float Yes
aileron_to_rudder_scale

The aileron to rudder ratio, used to link the two.

If set to a value other than 0, the rudder will be controlled by the aileron controller axis instead of the rudder controller axis. The scale defines the ratio between the aileron input applied to the rudder and the original aileron input.

Float Yes
aileron_span_outboard

The outboard aileron span, expressed as a Percent Over 100.

This is the ratio of wing length from the tip to the end of the aileron surface. A larger aileron will increase the roll moment of aileron deflection, but it will also increase the local drag generated by aileron deflection.

Float

Yes
rudder_limit

Angular limit in degrees (absolute values only) of the rudder and vtail combined control surface.

This should be the maximum rudder deflection angle possible and will be scaled down by the elasticity table and the rudder_maxangle_scalar.

Float Yes
rudder_trim_limit

Angular limit in degrees (absolute values only) of the rudder trim.

This deflection adds to the rudder deflection. This should be the maximum rudder trim deflection angle possible and will be scaled down by the elasticity table and the rudder_trim_effectiveness.

Float Yes
elevator_trim_limit

Angular limit in degrees of the elevator trim. This deflection adds to the elevator deflection. This should be the maximum elevator trim deflection angle possible and will be scaled down by the elasticity table and the elevator_trim_effectiveness. Note that this value can be overriden by the elevator_trim_up_limit and elevator_trim_down_limit parameters.

If this value is omitted and the elevator_trim_up_limit and elevator_trim_down_limit have not been set, then the default behavior will be to have no elevator trim applied.

Float No
elevator_trim_neutral

For many aircraft this will be the take off trim setting. The aircraft will start with this trim setting when starting on the ground. This trim setting is not used for performance normalizations nor to achieve the target lift and drag values, and is used for indicators only. The htail_incidence will be used for performance normalization.

Float Yes
elevator_trim_up_limit

Set the upper limit of the elevator trim deflection that makes the aircraft pitch up, in degrees (absolute values only). Note that this will override the value set in elevator_trim_limit, and will be scaled down by the elasticity table and the elevator_trim_effectiveness.

If this parameter is omitted, then the elevator_trim_limit value will be used, and if that parameter is also omitted, then the no elevator trim will be applied.

Float No
elevator_trim_down_limit

Set the lower limit of the elevator trim deflection that makes the aircraft pitch down, in degrees (absolute values only). Note that this value cannot be greater than the value set in elevator_trim_up_limit, and will override the value set in elevator_trim_limit. It will also be scaled down by the elasticity table and the elevator_trim_effectiveness.

If this parameter is omitted, then the elevator_trim_limit value will be used, and if that parameter is also omitted, then the no elevator trim will be applied.

Float No
spoiler_limit

This sets the angular limit of the wing spoilers on an aircraft, in degrees (absolute values only), when the spoiler is in ground configuration.

If this limit is 0, no spoilers exist for the aircraft.

flight_model_cfg.htm#
Float Yes
air_spoiler_limit

Angular limit in degrees of the spoiler and wing combined control surface, in degrees (absolute values only) when the spoiler is in the air configuration.

If this value is not set, then it will default to the spoiler_limit value.

Float Yes
spoilerons_available

Indicates whether the spoilers also behave as spoilerons for roll control (if spoilers are available): 0 = FALSE (no spoilerons) or 1 = TRUE.

Spoilerons will add spoiler deflection to aileron deflection based on aileron_to_spoileron_gain and min_ailerons_for_spoilerons.

Bool Yes
aileron_to_spoileron_gain Scales the spoileron deflection angle in relation to the aileron deflection angle set with min_ailerons_for_spoilerons (if spoilerons_available is TRUE). Float Yes
min_ailerons_for_spoilerons

This value is used to indicate at what minimum aileron deflection angle the spoilers become active for roll control, in degrees (absolute values only). Based on aileron_to_spoileron_gain.

Float Yes
min_flaps_for_spoilerons This value is used to indicate the minimum flap handle position where the spoilerons become active, in degrees (absolute values only). Float Yes
spoiler_extension_time Time, in seconds, necessary to fully extend the spoilers. Float Yes
spoiler_handle_available

This is used to configure the airplane with manual controls for the spoiler deflections (TRUE, 1) or not (FALSE, 0).

Bool Yes
spoiler_disabled_by_flaps If TRUE (1), the spoilers will automatically retract when the flaps are extended. Default is FALSE (0). Bool Yes
auto_spoiler_auto_retracts If TRUE (1), the spoilers will automatically retract when the plane speed goes below auto_spoiler_min_speed. Default is TRUE (1). Bool Yes
auto_spoiler_available Sets whether auto spoilers are available (TRUE, 1) or not (FALSE, 0). Bool Yes
auto_spoiler_min_speed The minimum speed (in Knots) at which auto spoiler can activate. Defaults to 0. Float Yes
positive_g_limit_flaps_up

Flap positive load limit when up. This is the positive limit - in G's - that is imposed on the aircraft when the flaps are up. The supplied value is multiplied by the load_safety_factor parameter before being compared to the current load factor to detect if the aircraft is beyond limits.

Note that if this parameter is not included, then none of the G-Limit flaps parameter will be read and will simply use the default values.

Default value is 4.

The aircraft will crash if the load factor reaches the G limit calculated using this parameter (For more information please see here: Overstress Damage). An aircraft with a load factor hold fly by wire system, will respect these limits as load factor limits.

Float Yes
positive_g_limit_flaps_down

Flap positive load limit when down. This is the positive limit - in G's - that is imposed on the aircraft when the flaps are down. The supplied value is multiplied by the load_safety_factor parameter before being compared to the current load factor to detect if the aircraft is beyond limits.

Note that this parameter is only read when the positive_g_limit_flaps_up has been defined.

Default value is 2.

The aircraft will crash if the load factor reaches the G limit calculated using this parameter (For more information please see here: Overstress Damage). An aircraft with a load factor hold fly by wire system, will respect these limits as load factor limits.

Float Yes
negative_g_limit_flaps_up

Flap negative load limit when up. This is the negative limit - in G's - that is imposed on the aircraft when the flaps are up. The supplied value is multiplied by the load_safety_factor parameter before being compared to the current load factor to detect if the aircraft is beyond limits.

Note that this parameter is only read when the positive_g_limit_flaps_up has been defined.

Default value is 1.5.

The aircraft will crash if the load factor reaches the G limit calculated using this parameter (For more information please see here: Overstress Damage). An aircraft with a load factor hold fly by wire system, will respect these limits as load factor limits.

Float Yes
negative_g_limit_flaps_down

Flap negative load limit when down. This is the negative limit - in G's - that is imposed on the aircraft when the flaps are down. The supplied value is multiplied by the load_safety_factor parameter before being compared to the current load factor to detect if the aircraft is beyond limits.

Note that this parameter is only read when the positive_g_limit_flaps_up has been defined.

flight_model_cfg.htm#

Default value is 1.5.

The aircraft will crash if the load factor reaches the G limit calculated using this parameter (For more information please see here: Overstress Damage). An aircraft with a load factor hold fly by wire system, will respect these limits as load factor limits.

Float Yes
load_safety_factor The load safety factor value. Float Yes
load_g_limiter_g

This is the multiplier on top of the design limits before which damage will begin to accrue. It is used by the autopilot and FBW systems as part of the pitch control limiter.

Default value is 7.5.

Float No
flap_to_aileron_scale The scale defines the ratio of aileron deflection based on flap deflection. Will deflect ailerons when flaps are extended. Float Yes
fly_by_wire

Sets whether fly-by-wire is available (TRUE, 1) or not (FALSE, 0).

A fly by wire control system disconnects the direct connection between yoke and rudder inputs and the control surfaces and adds a computer in between. This allows to activate control modes such as load factor hold.

NOTE: When enabled your aircraft may use the [STALL PROTECTION] system.

Bool Yes
fly_by_wire_from_flaps

Set's the fly-by-wire mode. When set to 0 (FALSE), the fly-by-wire will be in load factor hold mode above 50ft and in direct mode below 50ft. When set to 1 (TRUE), the fly-by-wire will be in load factor hold mode when flaps are retracted and in direct mode when flaps are extended.

Default is 0 (FALSE).

Bool No
elevator_elasticity_table

A table that allows you to scale down the elevator control surface deflection angle depending on the current dynamic pressure. The table has a maximum of 5 values and has the following format:

dynamic_pressure:correction_factor,
dynamic_pressure:correction_factor,
etc...

Pressure is expressed as psf and the yoke correction factor is a Percent Over 100.

The dynamic pressure being airspeed dependent, this allows to reduce deflection based on speed. The [Dev Mode] aircraft debugging tools allow you to get the current dynamic pressure from the Speed debug window. The dynamic pressure can also be obtained with the following formula:

$$\textrm{dynamicpressure} = 0.5 \times \textrm{airdensity} \times \textrm{airspeed} \times \textrm{airspeed}$$

Default value is: 0.0:1.0

1D Curve of Floats

No
aileron_elasticity_table

A table that allows you to scale down the aileron control surface deflection angle depending on the current dynamic pressure.

The table has a maximum of 5 values and has the following format:

dynamic_pressure:correction_factor,
dynamic_pressure:correction_factor,
etc...

Pressure is expressed as psf and the yoke correction factor is a Percent Over 100.

The dynamic pressure being airspeed dependent, this allows you to reduce deflection based on speed. The [Dev Mode] aircraft debugging tools allow you to get the current dynamic pressure from the Speed debug window. The dynamic pressure can also be obtained with the following formula:

$$\textrm{dynamicpressure} = 0.5 \times \textrm{airdensity} \times \textrm{airspeed} \times \textrm{airspeed}$$

Default value is: 0.0:1.0

1D Curve of Floats

No
rudder_elasticity_table

A table that allows you to scale down the rudder control surface deflection angle depending on the current dynamic pressure. The table has a maximum of 5 values and has the following format:

dynamic_pressure:correction_factor,
dynamic_pressure:correction_factor,
etc...

Pressure is expressed as psf and the yoke correction factor is a Percent Over 100.

The dynamic pressure being airspeed dependent, this allows to reduce deflection based on speed. The [Dev Mode] aircraft debugging tools allow you to get the current dynamic pressure from the Speed debug window. The dynamic pressure can also be obtained with the following formula:

$$\textrm{dynamicpressure} = 0.5 \times \textrm{airdensity} \times \textrm{airspeed} \times \textrm{airspeed}$$

Default value is: 0.0:1.0

1D Curve of Floats

No
elevator_trim_elasticity_table

A table that allows you to scale down the elevator control surface deflection angle depending on the current dynamic pressure. The table has a maximum of 5 values and has the following format:

dynamic_pressure:correction_factor,
dynamic_pressure:correction_factor,
etc...

Pressure is expressed as psf and the yoke correction factor is a Percent Over 100.

The dynamic pressure being airspeed dependent, this allows to reduce deflection based on speed. The [Dev Mode] aircraft debugging tools allow you to get the current dynamic pressure from the Speed debug window. The dynamic pressure can also be obtained with the following formula:

$$\textrm{dynamicpressure} = 0.5 \times \textrm{airdensity} \times \textrm{airspeed} \times \textrm{airspeed}$$

Default value is: 0.0:1.0

1D Curve of Floats

No
controls_reactivity_scalar

The reactivity scalar for all controls, which can be used to adjust - at a global level - the responsiveness and behaviour of the control system. This value is clamped to a maximum of 1, regardless of what the actual input is set to.

Float Yes
control_aileron_forcebased

If set to 1 (True), the control surface deflection will be based on an optional force simulation. When this simulation is on, use the elasticity table only for actual elasticity simulation, not to also simulate input force limit, or there will be a redundancy.

Default value is 0.

Boolean No
control_aileron_maxforce_student

Defines the maximum input force (in lbs) a student pilot is capable to hold.

Default value is 10.

Float No
control_aileron_minforce_student

Defines the minimum input force (in lbs) below a student pilot will input to work against input lag causing motion resisting forces in the input.

Default value is 1.

Float No
control_aileron_maxforce_pilot

Defines the maximum input force (in lbs) a pilot is capable to hold.

Default value is 20.

Float No
control_aileron_minforce_pilot

Defines the minimum input force (in lbs) below a pilot will input to work against input lag causing motion resisting forces in the input.

Default value is 2.

Float No
control_aileron_maxforce_testpilot

Defines the maximum input force (in lbs) a testpilot is capable to hold.

Default value is 40.

Float No
control_aileron_minforce_testpilot

Defines the minimum input force (in lbs) below a test pilot will input to work against input lag causing motion resisting forces in the input.

Default value is 4.

Float No
control_aileron_still_force_at_max

Defines the holding force (in lbs) required for a maximum deflection at zero airspeed.

Default value is 1.

Float No
control_aileron_still_force_to_move

Defines the moving force (in lbs/ratio/second) required for change the control surface deflection at zero airspeed.

Default value is 2.

Float No
control_aileron_dynpres_ratio_force_at_max

Defines ratio of the dynamic pressure that will be added to the required holding force in lbs.

Example: With a ratio of 1.0 and a dynamic pressure of 100, 100lbs of holding force will be required to maintain a 100% deflection.

Default value is 0.66.

Float No
control_aileron_dynpres_ratio_force_to_move

Defines ratio of the dynamic pressure that will be added to the required moving force in lbs/ration/second.

Example: With a ratio of 0.1 and a dynamic pressure of 100, 10lbs of moving force will be required over 1 second to move the deflection to 100% over 1 second.

Default value is 0.1.

Float No
control_aileron_neutral_return_force_scalar Float No
control_elevator_forcebased

If set to 1 (TRUE), the control surface deflection will be based on an optional force simulation. When this simulation is on, use the elasticity table only for actual elasticity simulation, not to also simulate input force limit, or there will be a redundancy.

Default value is 0.

Boolean No
control_elevator_maxforce_student

Defines the maximum input force (in lbs) a student pilot is capable to hold.

Default value is 20.

Float No
control_elevator_minforce_student

Defines the minimum input force (in lbs) below a student pilot will input to work against input lag causing motion resisting forces in the input.

Default value is 2.

Float No
control_elevator_maxforce_pilot

Defines the maximum input force (in lbs) a pilot is capable to hold.

Default value is 40.

Float No
control_elevator_minforce_pilot

Defines the minimum input force (in lbs) below a pilot will input to work against input lag causing motion resisting forces in the input.

Default value is 4.

Float No
control_elevator_maxforce_testpilot

Defines the maximum input force (in lbs) a testpilot is capable to hold.

Default value is 80.

Float No
control_elevator_maxforce_testpilot

Defines the minimum input force (in lbs) below a test pilot will input to work against input lag causing motion resisting forces in the input.

Default value is 8.

Float No
control_elevator_still_force_at_max

Defines the holding force (in lbs) required for a maximum deflection at zero airspeed.

Default value is 2.

Float No
control_elevator_still_force_to_move

Defines the moving force (in lbs/ratio/second) required for change the control surface deflection at zero airspeed.

Default value is 4.

Float No
control_elevator_dynpres_ratio_force_at_max

Defines ratio of the dynamic pressure that will be added to the required holding force in lbs.

Example: With a ratio of 1.0 and a dynamic pressure of 100, 100lbs of holding force will be required to maintain a 100% deflection.

Default value is 1.33.

Float No
control_elevator_dynpres_ratio_force_to_move

Defines ratio of the dynamic pressure that will be added to the required moving force in lbs/ratio/second.

Example: With a ratio of 0.1 and a dynamic pressure of 100, 10lbs of moving force will be required over 1 second to move the deflection to 100% over 1 second.

Default value is 0.2.

Float No
control_elevator_neutral_return_force_scalar

 

Boolean No
control_rudder_forcebased

If set to 1 (TRUE), the control surface deflection will be based on an optional force simulation. When this simulation is on, use the elasticity table only for actual elasticity simulation, not to also simulate input force limit, or there will be a redundancy.

Default value is 0.

Float No
control_rudder_maxforce_student

Defines the maximum input force (in lbs) a student pilot is capable to hold.

Default value is 40.

Float No
control_rudder_minforce_student

Defines the minimum input force (in lbs) below a student pilot will input to work against input lag causing motion resisting forces in the input.

Default value is 4.

Float No
control_rudder_maxforce_pilot

Defines the maximum input force (in lbs) a pilot is capable to hold.

Default value is 80.

Float No
control_rudder_minforce_pilot

Defines the minimum input force (in lbs) below a pilot will input to work against input lag causing motion resisting forces in the input.

Default value is 8.

Float No
control_rudder_maxforce_testpilot

Defines the maximum input force (in lbs) a testpilot is capable to hold.

Default value is 160.

Float No
control_rudder_minforce_testpilot

Defines the minimum input force (in lbs) below a test pilot will input to work against input lag causing motion resisting forces in the input.

Default value is 16.

Float No
control_rudder_still_force_at_max

Defines the holding force (in lbs) required for a maximum deflection at zero airspeed.

Default value is 4.

Float No
control_rudder_still_force_to_move

Defines the moving force (in lbs/ratio/second) required for change the control surface deflection at zero airspeed.

Default value is 8.

Float No
control_rudder_dynpres_ratio_force_at_max

Defines ratio of the dynamic pressure that will be added to the required holding force in lbs.

Example: With a ratio of 1.0 and a dynamic pressure of 100, 100lbs of holding force will be required to maintain a 100% deflection.

Default value is 2.66.

Float No
control_rudder_dynpres_ratio_force_to_move

Defines ratio of the dynamic pressure that will be added to the required moving force in lbs/ration/second.

Example: With a ratio of 0.1 and a dynamic pressure of 100, 10lbs of moving force will be required over 1 second to move the deflection to 100% over 1 second.

Default value is 0.4.

Float No
control_rudder_neutral_return_force_scalar Float No

 

 

[AERODYNAMICS]

This section is for defining the aerodynamics of an aircraft. In general, the aerodynamics of the aircraft should be created and edited through the SimObject Editor, and only tweaked if required through the flight_model.cfg file.

NOTE: This section is not required if you are creating a Helicopter SimObject.

 

Note that you can find further information on the physics behind this section from the following page:

 

You can also find a helpful tutorial on the basics of setting up the aircraft geometry from the following page:

 

The available parameters in the [AERODYNAMICS] section are:

 

Parameter Description Type Required
CFD_EnableSimulation

This can be used to enable (1, TRUE) or disable (0, FALSE) the use of CFD within the simulation.

Default value is 0 (FALSE).

For more information, please see here: Debug Aircraft CFD.

Boolean No
CFD_ReinjectBody

This can be used to enable (1, TRUE) or disable (0, FALSE) the reinjection of the CFD output with that of the flight model, specifically affecting the airframe surface. Note that this needs to be set to 1 (TRUE) for CFD_ReinjectRotors, CFD_ReinjectVTailX, and CFD_ReinjectHTailY to work as well. If this is 0 (FALSE), then those parameters will have no effect.

Default value is 0 (FALSE).

For more information, please see here: Debug Aircraft CFD.

Boolean No
CFD_ReinjectRotors

This can be used to enable (1, TRUE) or disable (0, FALSE) the re-injection of the CFD output with that of the flight model for rotors/propellers. Note that this parameter will have no effect if the CFD_ReinjectBody parameter is not set to 1 (TRUE).

Default value is 0 (FALSE).

For more information, please see here: Debug Aircraft CFD.
IMPORTANT! This requires that you have the prop_mod_use_modern parameter set to 1 (TRUE).

Boolean No
CFD_ReinjectVTailX

This can be used to enable (1, TRUE) or disable (0, FALSE) the re-injection of the CFD output with that of the flight model, specifically affecting the tail control surfaces. Note that this parameter will have no effect if the CFD_ReinjectBody parameter is not set to 1 (TRUE).

Default value is 0 (FALSE).

For more information, please see here: Debug Aircraft CFD.

Boolean No
CFD_ReinjectHTailY

This can be used to enable (1, TRUE) or disable (0, FALSE) the re-injection of the CFD output with that of the flight model, specifically affecting the tail control surfaces. Note that this parameter will have no effect if the CFD_ReinjectBody parameter is not set to 1 (TRUE).

Default value is 0 (FALSE).

For more information, please see here: Debug Aircraft CFD.

Boolean No
CFD_AirViscosity

Set the air viscosity when the CFD simulation is active. This is essentially the viscosity term of the Navier Stokes equations used by the CFD simulation, and it sets the rate at which the airspeed of a voxel will tend to the average airspeed of the surrounding voxels.

Default value is 0.05, and the value will only be used when the CFD_EnableSimulation parameter is set to 1 (TRUE).

For more information, please see here: Debug Aircraft CFD.

Float No
CFD_AirInCompressibility

Set the air incompressibility when the CFD simulation is active. This is essentially the divergence term of the the Navier Stokes equations used by the CFD simulation, and sets the rate at which the pressure of a voxel will be impacted by the local divergence.

Default value is 1.0, and the value will only be used when the CFD_EnableSimulation parameter is set to 1 (TRUE).

For more information, please see here: Debug Aircraft CFD.

Float No
CFD_VoxelSizeScale

Set the scale of the voxel volume for CFD simulation. At 1, this will create a volume that is 150% that of the aircraft wingspan, and the volume will be comprised of n³ voxels (where n is set by the CFD_VoxelNbVoxels parameter).

Default value is 1.0, and the value will only be used when the CFD_EnableSimulation parameter is set to 1 (TRUE).

For more information, please see here: Debug Aircraft CFD.

Float No
CFD_VoxelNbVoxels

This can be used to set the number of voxels that will be cubed to make the sample volume for the CFD simulation.

IMPORTANT! This may have a serious impact on performance if set to values greater than the default value, due to it currently having a time complexity of O(n3).

Default value is 20.0, and the value will only be used when the CFD_EnableSimulation parameter is set to 1 (TRUE).

For more information, please see here: Debug Aircraft CFD.

Float No
CFD_GroundCollisionVoxelOffset

This parameter allows you to offset the ground collision vertically by N voxels. With a value of 0 voxels, the ground collision lets the air penetrate up to 1 voxel into the ground, ie: the ground is a "soft collision layer" of about 1 voxel thickness that starts at ground level and ends 1 voxel into the ground. By setting this to 1 voxel, the soft ground collision starts 1 voxel above the ground and stops airflow before it touches the ground. Adjusting this value will have an impact on the strength of the ground effect that is applied on the aircraft. It is worth noting that ground effect is calculated taking into account the ground conditions, so things like icing will have an effect on the drag and lift.

Default value is 0.0, and the value will only be used when the CFD_EnableSimulation parameter is set to 1 (TRUE).

For more information, please see here: Debug Aircraft CFD.

Float No
lift_coef_pitch_rate

Defines how much lift will be added to the overall lift formula based on the current pitch rotation speed.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section.

Float Yes if using legacy flight model, No otherwise.
lift_coef_daoa

Defines how much lift will be added to the overall lift formula based on the current angle of attack variation rate.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section.

Float Yes if using legacy flight model, No otherwise.
lift_coef_delta_elevator

Defines how much lift will be added to the overall lift formula based on the current elevator deflection angle.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section.

Float Yes if using legacy flight model, No otherwise.
lift_coef_horizontal_incidence

Defines how much lift will be added to the overall lift formula based on the current yaw angle of the aircraft.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section.

Float Yes if using legacy flight model, No otherwise.
lift_coef_flaps Defines the lift coefficient that will be added to the target lift coefficient obtained with the lift_coef_aoa_table of the airplane when at maximum flap expansion. Float Yes
lift_coef_spoilers

Defines the lift coefficient that will be added to the target lift coefficient obtained with the lift_coef_aoa_table of the aircraft when at maximum spoiler expansion on the ground. This allows you to correctly tune the spoilers for ground usage where there is very strong drag and very strong loss in lift. Essentially this is the coefficient for the deflection of 1 radian.

 

The lift value is multiplied by the spoiler deflection in radians, so this coefficient is necessary to compensate for the scale by the deflection angle (also in radians), in order to reach 100%.

NOTE: This value will also be used when the aircraft is airborne, unless the lift_coef_air_spoilers value is set.

Float Yes
lift_coef_air_spoilers

Defines the lift coefficient that will be added to the target lift coefficient obtained with the lift_coef_aoa_table of the aircraft when at maximum spoiler expansion in the air. This allows to correctly tune the spoiler behaviour in the air where you have strong drag, and little loss in lift. The lift value is multiplied by the spoiler deflection in radians, so this coefficient is necessary to compensate for the scale by the deflection angle (also in radians), in order to reach 100%.

NOTE: This value overrides the value set by lift_coef_spoilers.

Float No
drag_coef_zero_lift

Defines the target drag of the airplane in clean configuration (ie: no propeller, no turbulence, no engine wash, no gears, no flaps, no spoilers, no deflections...), when there is zero lift. This is usually also called the \(C_{D0}\) or \(C_{DZeroLift}\). Zero lift may occur at an angle of attack of zero - reason for which \(C_{D0}\) is sometimes the drag at an AoA of 0 - but most of the time, zero lift occurs at an angle of attack that is negative and the \(C_{D0}\) does not correspond to the drag at AoA 0.

In the legacy FSX flight model, this defines the actual \(C_{D0}\). In the modern flight model, this defines the target \(C_{D0}\) that will be distributed over all the surfaces of the aircraft when building the airplane used in the aerodynamic surface simulation. Once the aircraft is built, it will then be normalized to match exactly the target \(C_{D0}\).

Float Yes
drag_coef_flaps Defines the target drag added when flaps are fully extended. In the legacy FSX flight model, this defines the actual flap drag. In the modern flight model, this defines the target flap drag that will be distributed over all the flap surfaces of the aircraft when building the airplane used in the aerodynamic surface simulation. Once the aircraft is built, it will then be normalized to match exactly the target flap drag. Float Yes
drag_coef_gear

Defines the drag of the gears that will be applied at the location of the gear contact points and create the appropriate angular moment.

If the aircraft features retractable gears, this coefficient will be zero once the gears are retracted. For non retractable gears this will always be present. All aircraft which feature gears, retractable or not, should define a drag coefficient for gears. This drag coefficient should not be baked into the drag_coef_zero_lift otherwise the gear angular moment calculations will be wrong. Also note that if the aircraft has no landing gear, this value will STILL have an effect and as such should be set to 0 in those cases.

Float Yes
drag_coef_spoilers

Defines the target drag added when spoilers are fully extended on the ground, where there is very strong drag and very strong loss in lift. The drag value is multiplied by the spoiler deflection in radians, so this coefficient is necessary to compensate for the scale by the deflection angle (also in radians), in order to reach 100%.

NOTE: This value will also be used when the aircraft is airborne, unless the drag_coef_air_spoilers value is set.In the legacy FSX flight model, this defines the actual flap drag. In the modern flight model, this defines the target spoiler drag that will be distributed over all the spoiler surfaces of the aircraft when building the airplane used in the aerodynamic surface simulation. Once the aircraft is built, it will then be normalized to match exactly the target spoiler drag.

Float Yes
drag_coef_air_spoilers

Defines the target drag added when spoilers are fully extended in the air, where you have strong drag, and little loss in lift. The drag value is multiplied by the spoiler deflection in radians, so this coefficient is necessary to compensate for the scale by the deflection angle (also in radians), in order to reach 100%.

NOTE: This value overrides the value set by drag_coef_spoilers.

Float Yes
StallDef_StartRatio

Ratio of the stall AoA at which the airflow will start detaching from the wing.

Default value is: 0.9

Float No
StallDef_EndRatio

Ratio of the stall AoA at which the airflow will be completely detached from the wing.

Default value is: 1.1

Float No
StallDef_CurvePower

Power of the ratio curve that controls the airflow detaching from the wing between start and end.

Default value is: 0.8

Float No
StallDef_minTransition

In Radians, minimum angle between the stall AoA at which the airflow starts detaching and at which it is fully detached.

Default value is: 0.025

Float No
StallDef_airflowdetachspeed

In ratios per second, speed at which the airflow will be detaching.

Default value is: 1.0

Float No
StallDef_airflowattachspeed

In ratios per second, speed at which the airflow will be attaching.

Default value is: 1.0

Float No
Stall_AileronAddIncidence

Degrees added to the stall AoA at the ailerons.

Default value is: 0.0

Float No
Stall_TipAddIncidence

Degrees added to the stall AoA at the wingtips.

Default value is: 2.0

Float No
Stall_TipAddTwist

Virtual added wing twist to reduce stall at the wingtips.

Default value is: 2.5

Float No
Stall_TipTwistScaleRatio

Scale ratio of the virtual added wing twist.

Default value is: 0.9

Float No
stallalpha

Defines the theoretical average alpha (AoA) at which the aircraft will stall, in degrees.

If the parameter is omitted from the file, then - when the aircraft is first instantiated - the stall alpha is measured on the actual flight model by performing lift measures at various AoA to find the point where the lift goes down when the AoA goes up. This precalculated value will be used as the default value.

Float No
stallalpha_ff

Defines the theoretical average alpha (AoA) at which the aircraft will stall in full-flap configuration, in degrees.

If the parameter is omitted from the file, then - when the aircraft is first instantiated - the stall alpha is measured on the actual flight model by performing lift measures at various AoA to find the point where the lift goes down when the AoA goes up. This precalculated value will be used as the default value.

Float No
fuselage_rigidity

This parameter sets the rigidity of the fuselage. If set to -1 then the fuselage will be considered as having "infinite" rigidity, while values greater than 0 will mean that applied forces will affect the airframe. The approximate value for this parameter can be calculated as follows:

  • fuselage_rigidity = distance from the CG in ft at which a force applied yields 50% of it's effect on the entire airframe after 1 second.

Note that low rigidity will increase the aircraft oscillations, and if the rigidity is low enough for the time accumulation to correspond to the oscillation frequency, then you can even get a situation of resonance that will cause the entire airframe to "flutter" wildly.

Default value is -1, and the value is in ft.

Float No
fuselage_inertia

This parameter sets the inertia for the fuselage, and works in harmony with the fuselage_rigidity parameter. However, if that parameter is less than or equal to zero, then this parameter will have no effect. Generally you want to set this to 1 to start with then tweak it up or down to get the aircraft behaviour that you require.

Default value is 1.

Float No
presspt_fwd_Alpha0_pMAC Defines an additional forward offset applied to the overall pressure center of the wing when the wing surface is at an AoA of 0. The offset is defined as a ratio of the local Mean Aerodynamic Chord and negative values indicate a backwards offset. Float No
presspt_fwd_AlphaStall_pMAC Defines an additional forward offset applied to the overall pressure center of the wing when the wing surface is at an the stall AoA. The offset is defined as a ratio of the local Mean Aerodynamic Chord and negative values indicate a backwards offset. Float No
presspt_fwd_AlphaHiStall_pMAC Defines an additional forward offset applied to the overall pressure center of the wing when the wing surface is at high above the stall AoA (during a stall). The offset is defined as a ratio of the local Mean Aerodynamic Chord, and negative values indicate a backwards offset. Float No
side_force_slip_angle

Defines how much side force will be generated when the yaw angle is non zero (during a side slip).

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use fuselage_lateral_cx to modify the side drag coefficient of the fuselage and rudder_lift_coef to modify the forces generated by the rudder.

Float Yes
side_force_roll_rate

Defines how much side force will be generated when the aircraft has some roll speed (during a roll).

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, the side force resulting from a roll is a complex combination of the effect of all the aircraft surfaces that cannot be directly controlled. Making sure the aircraft surfaces are correctly aligned and feature correct areas and coefficients will result in a realistic side force when rolling.

Float Yes if using legacy flight model, No otherwise.
side_force_yaw_rate

Defines how much side force will be generated when the yaw angle is changing.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use fuselage_lateral_cx to modify the side drag coefficient of the fuselage and rudder_lift_coef to modify the forces generated by the rudder.

Float Yes if using legacy flight model, No otherwise.
side_force_delta_rudder

Defines how much side force will be generated when the rudder is deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use rudder_lift_coef to modify the forces generated by the rudder deflection.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_horizontal_incidence

Defines how much pitch moment will be generated when the aircraft is yawing.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the rudder trim and, rudder area and rudder vertical position to modify the pitch moment generated generated by the rudder at zero deflection.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_delta_elevator

Defines how much pitch moment will be generated when the elevator is deflected.

This is a legacy FSX parameter and the actual value here is not normally used in the modern flight model, but the sign of the value is used and it is necessary to set a value other than 0 for the autopilot (see the notes below). In the modern flight model the effect that this parameter is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the elevator_lift_coef, elevator longitudinal position and elevator area to adjust this effect.

NOTE: The absolute value of this parameter is ignored by the modern flight model but it's sign is used to invert the elevator input angle when it is negative. This may be useful for aircraft that need an inverted elevator (elevator in the front).

NOTE: Even in the modern flight model, the autopilot system may still use this variable to calculate the elevator deflection necessary to find a required pitch moment. The PID will usually compensate for wrong values, but this variable cannot be set to zero or very far off and must be relatively close to reality. You can use the legacy flight model tool to calculate the correct value that will then usually work with the autopilot.

Float Yes
pitch_moment_delta_trim

Defines how much pitch moment will be generated when the elevator trim is deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the elevator_lift_coef, elevator longitudinal position and elevator area and scale the trim effect to adjust this effect.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_pitch_damping

Defines how much the pitch velocity will be dampened when the plane is pitching.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the elevator_lift_coef, elevator longitudinal position, fuselage_lateral_cx, and elevator area to adjust this effect. The wings and even the rudder may also contribute to this effect.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_aoa_0

Defines how much the pitch moment will be generated at AoA 0.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the htail_incidence as the primary variable to impact the 0 AoA pitch moment.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_daoa

Defines how much the alpha velocity will be dampened when the plane is changing incidence.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the elevator_lift_coef, elevator longitudinal position, fuselage_lateral_cx and elevator area to adjust this effect. The wings and even the rudder may also contribute to this effect.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_flaps

Defines how much pitch moment will be generated when the flaps will be deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, refer to the flaps documentation to see how to move the flap lift on the longitudinal axis in order to control the pitch moment at each flap level.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_gear

Defines how much the pitch moment will be generated because of the gears.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the drag_coef_gear and the position of the gear contact points to change the angular moments generated by gears.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_spoilers

Defines how much pitch moment will be generated when the spoilers will be deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, this will be automatically simulated and there is no way yet to change the pitch moment generated by spoilers. It will be an automatic effect of the spoiler deflection and mostly dependent on the drag generated by the spoilers and the vertical position of the wings.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_delta_elevator_propwash

Defines how much pitch moment will be generated when the elevator is deflected and there is a propeller spinning (prop wash).

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model this is automatically simulated based on how air is accelerated by the propeller and blown onto the control surfaces. However one can use the elevator_lift_coef, elevator longitudinal position and elevator area to adjust this effect. In the modern flight model, this effect only works if the propeller is blowing air onto the control surfaces. If the propeller is under a wing, far from any surface, this effect will not occur.

Float Yes if using legacy flight model, No otherwise.
pitch_moment_pitch_propwash

Defines how much pitch moment will be generated when the plane is pitching and there is a propeller spinning (prop wash).

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model this is automatically simulated based on how air is accelerated by the propeller and blown onto the control surfaces. However one can use the elevator_lift_coef, elevator longitudinal position and elevator area to adjust this effect. In the modern flight model, this effect only works if the propeller is blowing air onto the control surfaces. If the propeller is under a wing, far from any surface, this effect will not occur.

Float Yes if using legacy flight model, No otherwise.
roll_moment_slip_angle

Defines how much roll moment will be generated when the aircraft is yawing or side slipping.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, most of the roll will be induced by the difference in lift between one wing and the other, and the rudder will work against this effect. Adjust the shape of the wing via wing_sweep, wing_dihedral, wing_twist, wing_camber, the position of the wing, and the vertical position of the rudder, the rudder area and rudder lift coefficient to adjust this effect. Some of these parameters will work against each other. Induced roll is a very complex effect to balance which will depend on many factors.

Float Yes if using legacy flight model, No otherwise.
roll_moment_roll_damping

Defines how much the roll speed will be dampened based on the current roll speed.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, most of the roll damping will be the result of the wings, the elevator and the rudder resisting roll. You can also use roll_stability and roll_gyro_stability to add more roll damping.

Float Yes if using legacy flight model, No otherwise.
roll_moment_yaw_rate

Defines how much roll moment will be generated when the aircraft is rotating around the yaw axis.

 

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, most of the roll will be induced by the difference in lift between one wing and the other, and the rudder will work against this effect. Adjust the shape of the wing via wing_sweep, wing_dihedral, wing_twist, wing_camber, the position of the wing, and the vertical position of the rudder, the rudder area and rudder lift coefficient to adjust this effect. Some of these parameters will work against each others. Induced roll is a very complex effect to balance which will depend on many factors.

Float Yes if using legacy flight model, No otherwise.
roll_moment_spoilers

Defines how much roll moment will be generated when the spoilers will be deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, this will be automatically simulated and there is no way yet to change the roll moment generated by spoilers.

Float Yes if using legacy flight model, No otherwise.
roll_moment_delta_aileron

Defines how much roll moment will be generated when the ailerons are deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the aileron_span_outboard, aileron_effectiveness and the aileron up and down angles to control this effect.

Float Yes if using legacy flight model, No otherwise.
roll_moment_delta_rudder

Defines how much roll moment will be generated when the rudder is deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, most of the roll will be induced by the difference in lift between one wing and the other, and the rudder will work against this effect. Adjust the shape of the wing via wing_sweep, wing_dihedral, wing_twist, wing_camber, the position of the wing, and the vertical position of the rudder, the rudder area and rudder lift coefficient to adjust this effect. Some of these parameters will work against each other. Induced roll is a very complex effect to balance which will depend on many factors.

Float Yes if using legacy flight model, No otherwise.
roll_moment_delta_aileron_trim_scalar

Defines how much roll moment will be generated when the aileron trim is are deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the aileron_span_outboard, aileron_trim_effectiveness and aileron up and down angles to control this effect.

Float Yes if using legacy flight model, No otherwise.
yaw_moment_slip_angle

Defines how much yaw moment will be generated when the aircraft is yawing or side slipping.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use fuselage_lateral_cx to modify the side drag coefficient of the fuselage and rudder_lift_coef to modify the forces generated by the rudder. The longitudinal position of the fuselage and rudder will have a big impact on the yaw moment. If most of the fuselage is behind the CG, the fuselage will have a stabilizing effect.

Float Yes if using legacy flight model, No otherwise.
yaw_moment_roll

Defines how much yaw moment will be generated when the aircraft has some roll speed (during a roll).

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, the yaw moment resulting from a roll is a complex combination of the effect of all the aircraft surfaces that cannot be directly controlled. Adjusting the rudder surface parameters will have the largest effect here but the wing will have an effect too. Making sure the aircraft surfaces are correctly aligned and feature correct areas and coefficients will result in a realistic yaw moment when rolling.

Float Yes if using legacy flight model, No otherwise.
yaw_moment_yaw_damping

Defines how much the yaw speed will be dampened based on the current yaw speed.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, most of the yaw damping will be the result of the rudder and fuselage, but the wings contribute as well. You can also use yaw_stability and yaw_gyro_stability to add more yaw damping.

Float Yes if using legacy flight model, No otherwise.
yaw_moment_yaw_propwash

Defines how much yaw moment will be generated when the plane is yawing and there is a propeller spinning (prop wash).

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model this is automatically simulated based on how air is accelerated by the propeller and blown onto the control surfaces. However one can use the rudder_lift_coef, rudder longitudinal position and rudder area to adjust this effect. In the modern flight model, this effect only works if the propeller is blowing air onto the control surfaces. If the propeller is under a wing, far from any surface, this effect will automatically not occur.

Float Yes if using legacy flight model, No otherwise.
yaw_moment_delta_aileron

Defines how much yaw moment will be generated when the ailerons are deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, this will mostly be caused by a difference in drag between both wings because of the difference in airspeed between both wings and the difference in deflection of both ailerons. Use the aileron_up_drag_coef, aileron_down_drag_coef and aileron up & down angles to control this effect.

Float Yes if using legacy flight model, No otherwise.
yaw_moment_delta_rudder

Defines how much yaw moment will be generated when the rudder is deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use rudder_lift_coef to modify the moment generated by the rudder deflection. The longitudinal position of the rudder also plays an important role.

Float Yes if using legacy flight model, No otherwise.
yaw_moment_delta_rudder_propwash

Defines how much yaw moment will be generated when the plane rudder is deflected and there is a propeller spinning (prop wash).

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model this is automatically simulated based on how air is accelerated by the propeller and blown onto the control surfaces. However one can use the rudder_lift_coef, rudder longitudinal position and rudder area to adjust this effect. In the modern flight model, this effect only works if the propeller is blowing air onto the control surfaces. If the propeller is under a wing, far from any surface, this effect will automatically not occur.

Float Yes if using legacy flight model, No otherwise.
yaw_moment_delta_rudder_trim_scalar

Defines how much yaw moment will be generated when the rudder trim is are deflected.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, use the rudder_trim_effectiveness, rudder area and rudder max deflection to control this.

Float Yes if using legacy flight model, No otherwise.
compute_aero_center

Defines if the aerodynamic center longitudinal position should be placed computationally or manually. In legacy FSX, the aerodynamic center was in a constant position and computed based on the pitch moment data and moment of inertia values. This would still work with the modern flight model, but we recommend disabling the computation of the aerodynamic center - setting it to 0 (FALSE) - and positioning this manually with aero_center_lift.

Float Yes
aero_center_lift

When compute_aero_center is set to 0 (FALSE) this variable allows you to define the longitudinal position of the aerodynamic center, expressed in ft. The modern flight model does not force the position of the aerodynamic center during the simulation because the aerodynamic center is not static in this flight model - it is calculated as the result of complex pressure forces applied on the surfaces, which actually causes a moving aerodynamic center. It is, however, usually very close to 25% and will normally move between 20% and 30%. So, we use this variable to longitudinally align the wing surfaces with the wing geometry, considering that the aerodynamic center is located at 25% MAC. Again, this does not mean that the aero center will then stay at 25% MAC during the simulation, it will just be used to initialize the surface position once at start.

IMPORTANT! This is positioned relative to the (0,0,0) position in the 3D model reference, not the Reference Datum position.

Float Yes
aileron_up_drag_coef

Defines the drag added by upwards aileron deflection. This parameter has a significant impact on adverse yaw. Reduce upward deflection drag to get more adverse yaw. This parameter is multiplied by the aileron deflection angle and internal coefficients.

Default is 0.5. This can be scaled with the aileron_up_drag_scalar parameter in the [FLIGHT_TUNING] section and is further modified by internal coefficients.

Float No
aileron_down_drag_coef

Defines the drag added by upwards aileron deflection. This parameter has a significant impact on adverse yaw. Increase downward deflection drag to get more adverse yaw. This parameter is multiplied by the aileron deflection angle.

Default is 1. This can be scaled with the aileron_down_drag_scalar parameter in the [FLIGHT_TUNING] section and is further modified by internal coefficients.

Float No
elevator_lift_coef

Defines the lift coefficient slope of the elevator control surface. This will have a direct impact on elevator authority and pitch stability. The elevator lift coefficient slope is usually dependent on the elevator aspect ratio.

Default is 5.0, and generally values will always fall between 1.0 and 5.0, with a theoretical maximum of 2𝝅 and a recommended value between 2.0 (for less authority and stability) and 5.0 (for more authority and stability). This can be scaled with the elevator_effectiveness parameter in the [FLIGHT_TUNING] section.

Float No
rudder_lift_coef

Defines the lift coefficient slope of the rudder control surface. This will have a direct impact on rudder authority, yaw stability, adverse yaw and induced roll. The rudder lift coefficient slope is usually dependent on the rudder aspect ratio.

Default is 5.0, and generally values will always fall between 1.0 and 5.0, with a theoretical maximum of 2𝝅 and a recommended value between 2.0 (for less authority and stability) and 5.0 (for more authority and stability). This can be scaled with the rudder_effectiveness parameter in the [FLIGHT_TUNING] section.

Float No
lift_coef_aoa_table

This table allows you to define the AoA polar (in radians) against the clean aircraft lift coefficient. The AoA vs. lift table defines how much lift the aircraft generates at various AoAs. The table has a maximum of 47 entries with the following format:

AoA_alpha:lift_coef,
AoA_alpha:lift_coef,
AoA_alpha:lift_coef,
etc...

In the modern flight model, this is used during the aircraft surfaces construction as a lift target that the aircraft should achieve at various angles of attack. This will impact the wing surfaces only, but the total lift will consider all surfaces. It describes the lift in clean configuration (ie: zero slip, no propeller, no gears, no control surface deflection). Once the aircraft is created, if will be normalized so that the effective lift coefficients measured actually match the target lift coefficients.

NOTE: The lift coefficients are only matched between AoAs 0 and the stall AoA. For other AoAs all around the 360° of the polar, it will be a natural consequence of the setup of the aerodynamic surfaces and other parameters. The polar does not need to be accurately defined in detail for AoAs outside of the -10° to stall +10° range in this table.

1D Curve of Floats Yes
lift_coef_ground_effect_mach_table

This table allows you to scale the ground effect intensity. This defines the maximum ground effect on the lift component but will impact the maximum effect on the induced drag component proportionally as well. Even though this table allows you to define the ground effect at various mach levels, it is the primary way to set the ground effect intensity. The table has a maximum of 11 entries and the format:

mach:lift_coef,
mach:lift_coef,
mach:lift_coef,
etc...
1D Curve of Floats Yes
lift_coef_mach_table

Scales the lift coefficient based on the mach level. The table permits a maximum of 17 entries and has the following format:

mach:lift_coef,
mach:lift_coef,
mach:lift_coef,
etc...

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section.

1D Curve of Floats

Yes
lift_coef_delta_elevator_mach_table

Scales the delta elevator lift coefficient based on the mach level. The table has a maximum of 17 entries and the format:

mach:lift_coef,
mach:lift_coef,
mach:lift_coef,
etc...

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
lift_coef_daoa_mach_table

Scales the lift coefficient impacted by the change in AoA based on the mach level. The table has a maximum of 17 entries and the format:

mach:lift_coef,
mach:lift_coef,
mach:lift_coef,
etc...

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, the lift coefficient at higher mach levels is automatically impacted by a progressive detaching of the laminar airflow over the surfaces.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
lift_coef_pitch_rate_mach_table

Scales the lift coefficient impacted by the change in pitch based on the mach level. The table has a maximum of 17 entries and the format:

mach:lift_coef,
mach:lift_coef,
mach:lift_coef,
etc...

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, the lift coefficient at higher mach levels is automatically impacted by a progressive detaching of the laminar airflow over the surfaces.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
lift_coef_horizontal_incidence_mach_table

Scales the lift coefficient impacted by the change in yaw based on the mach level. The table has a maximum of 17 entries and the format:

mach:lift_coef,
mach:lift_coef,
mach:lift_coef,
etc...

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model this effect is natively obtained through aerodynamic simulation of the surfaces defined in the [AIRPLANE_GEOMETRY] section. In the modern flight model, the lift coefficient at higher mach levels is automatically impacted by a progressive detaching of the laminar airflow over the surfaces.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
drag_coef_zero_lift_mach_tab

Adds drag based on the mach level. In the modern flight model, the drag coefficient at higher mach levels is automatically impacted by a progressive detaching of the laminar airflow over the surfaces. However this table allows to add more drag at specific mach levels to simulate a mach wall or specific effects of drag due to turbulence at specific drag levels. Drag walls are not natively simulated yet and will need to be defined with this table. The table has a maximum of 17 entries and the format:

mach:drag_coef,
mach:drag_coef,
mach:drag_coef,
etc...

1D Curve of Floats

Yes
side_force_slip_angle_mach_table Legacy FSX table, not used in the modern flight model.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
side_force_delta_rudder_mach_table Legacy FSX table, not used in the modern flight model.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
side_force_yaw_rate_mach_table Legacy FSX table, not used in the modern flight model.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
side_force_roll_rate_mach_table Legacy FSX table, not used in the modern flight model.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
pitch_moment_aoa_table

Influence CoL computation if not prescribed

Legacy FSX table, not used in the modern flight model.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
pitch_moment_delta_elevator_aoa_table

AoA(alpha) is given in DEGREES

Legacy FSX table, not used in the modern flight model.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
pitch_moment_horizontal_incidence_aoa_table

AoA(alpha) is given in DEGREES

Legacy FSX table, not used in the modern flight model.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
pitch_moment_daoa_aoa_table

AoA(alpha) is given in DEGREES

Legacy FSX table, not used in the modern flight model.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
pitch_moment_pitch_alpha_table

AoA(alpha) is given in DEGREES

Legacy FSX table, not used in the modern flight model.

1D Curve of Floats

Yes if using legacy flight model, No otherwise.
pitch_moment_delta_elevator_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
pitch_moment_daoa_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
pitch_moment_pitch_rate_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
pitch_moment_horizontal_incidence_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
pitch_moment_aoa_0_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
roll_moment_aoa_table

\({C_L}\) (roll moment coefficient) versus AoA

Legacy FSX table, not used in the modern flight model.

1D Curve of Floats Yes if using legacy flight model, No otherwise.
roll_moment_slip_angle_aoa_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
roll_moment_roll_rate_aoa_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
roll_moment_delta_aileron_aoa_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
roll_moment_slip_angle_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
roll_moment_delta_rudder_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
roll_moment_delta_aileron_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
roll_moment_yaw_rate_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
roll_moment_roll_rate_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
yaw_moment_aoa_table

\({C_n}\) (yaw moment coef) versus AoA.

Legacy FSX table, not used in the modern flight model.

1D Curve of Floats Yes if using legacy flight model, No otherwise.
yaw_moment_slip_angle_aoa_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
yaw_moment_delta_rudder_aoa_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
yaw_moment_slip_angle_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
yaw_moment_delta_rudder_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
yaw_moment_delta_aileron_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
yaw_moment_yaw_rate_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
yaw_moment_roll_rate_mach_table Legacy FSX table, not used in the modern flight model. 1D Curve of Floats Yes if using legacy flight model, No otherwise.
elevator_scaling_table

Allows you to define a non linear elevator deflection curve on top of the input curve settings possible in the simulator. The table defines how the input value is scaled for each range of input values. The table has the following format (maximum 17 value pairs):

elevator_angle:scale,
elevator_angle:scale,
elevator_angle:scale,
etc...

Default is to scale all input values by 1, and that the angles should be expressed in radians.

1D Curve of Floats Yes
aileron_scaling_table

Allows to define a non linear aileron deflection curve on top of the input curve settings possible in the simulator. The table defines how the input value is scaled for each range of input values. The table has the following format (maximum 17 value pairs):

aileron_angle:scale,
aileron_angle:scale,
aileron_angle:scale,
etc...

Default is to scale all input values by 1, and that the angles should be expressed in radians.

1D Curve of Floats Yes
rudder_scaling_table

Allows to define a non linear rudder deflection curve on top of the input curve settings possible in the simulator. The table defines how the input value is scaled for each range of input values. The table has the following format (maximum 17 value pairs):

rudder_angle:scale,
rudder_angle:scale,
rudder_angle:scale,
etc...

Default is to scale all input values by 1, and that the angles should be expressed in radians.

1D Curve of Floats Yes
aileron_load_factor_effectiveness_table

Scaling of roll_moment_delta_aileron versus gravity forces.

Legacy FSX table, not used in the modern flight model.

1D Curve of Floats Yes if using legacy flight model, No otherwise.
lift_coef_at_drag_zero

When building the surfaces of the aircraft, the modern flight model allows us to use the following drag formula:

\({C_D} = {C_{D0}} + K(C_L - C_{L0})^{2}\)

This parameter represents the \({C_{L0}}\) parameter of this formula in the clean configuration. The aircraft is built trying to match this drag polar and then a normalization pass is done on all surfaces to perfectly match the target polar. This parameter has also been added to the legacy FSX flight model that now also allows \({C_{D0}}\) to not be always zero.

Float Yes
lift_coef_at_drag_zero_flaps

When building the surfaces of the aircraft, the modern flight model allows us to use the following drag formula:

\({C_D} = {C_{D0}} + K(C_L - C_{L0})^{2}\)

This parameter represents the \({C_{L0}}\) parameter of this formula in the landing configuration with flaps fully deployed. The aircraft is built trying to match this drag polar and then a normalization pass is done on all surfaces to perfectly match the target polar. This parameter has also been added to the legacy FSX flight model that now also allows \({C_{D0}}\) to not be always zero.

Float Yes
fuselage_lateral_cx

Defines the perpendicular drag coefficient of the fuselage, which occurs when the airflow is going perpendicular to the front axis (ie: sideways - left to right or right to left) but also going up and down. This coefficient has an impact on drag when side slipping, as well as a general impact on yaw stability and pitch stability. Faster aircraft with a larger reynolds number should usually have a larger lateral fuselage \(C_x\).

Please note that the drag calculation supposes that the fuselage shape seen from the side has the shape of a rectangle with skewed front and rear tips. A larger or smaller \(C_x\) may be necessary to compensate for different fuselage shapes. If the fuselage has edges and is different from a perfect cylinder, the \(C_x\) should be higher. If the fuselage's area, when seen from the side, is smaller than the area of a skewed rectangle, the \(C_x\) should be smaller to compensate. A longer aircraft, with a higher l/d ratio, will have a higher \(C_x\). A shorter aircraft with a smaller l/d ratio, will have a smaller \(C_x\). Therefore, when chosing a \(C_x\) it is important to consider the reynolds number and l/d ratio of the fuselage.

Default is 0.4 - which is approximately the lateral drag of a cylinder with a reynolds number of a small aircraft and a l/d ratio of about 5, compensated for the shape of most small aircraft fuselages. The value should usually fall between 0.2 and 1.2 for most aircraft (with a "soft" limit of 2, which would essentially be a box).

Float No

 

 

[FLIGHT_TUNING]

This section is for tuning various aspects of the flight model for an aircraft.

NOTE: This section is not required if you are creating a Helicopter SimObject.

 

The available parameters are:

 

Parameter Description Type Required
modern_fm_only

This can be set to 1 (true) to force the aircraft to use the modern flight model, regardless of what the user may have selected in the Microsoft Flight Simulator 2024 options.

Default value is 0 (false).

Boolean No
legacy_fm_only

This can be set to 1 (true) to force the aircraft to use the legacy flight model, regardless of what the user may have selected in the Microsoft Flight Simulator 2024 options.

Default value is 0 (false).

Boolean No
legacy_fm_new_integration

This is only applicable to those aircraft that are using the legacy Flight Model. It was discovered that there was an issue with the acceleration integration calculations for the legacy flight model, and so this parameter exists to fix that. When set to 1 (true) the calculations will be correct, which may affect the handling of aircraft that have been calibrated using the "broken" flight model. When set to 0, the flight model will be the original one without the fix.

Default value is 0 (false).

Boolean No
empty_CG_deviation_limit

This value allows you to define - in ft - a limit to the maximum deviation that will be allowed in the weight & balance UI menu (where users can change the empty CG position).

Default value is infinite, and it can also can accept 0.

Float No
icing_scalar

With this value you can scale up or down the effects of icing on the plane. This will affects the effect of icing on lift and on the weight.

The default value is 1.0 (100% of the effect). Can accept 0.0 to remove all effects of icing.

Float No
cruise_lift_scalar

Scales the target lift coefficient as looked up from lift_coef_aoa_table over the entire range of AoAs.

Default value is 1.

Float No
parasite_drag_scalar

Scales the target drag coefficient as defined in drag_coef_zero_lift.

Default value is 1.

Float No
induced_drag_scalar

Scales the induced drag target as defined by the target induced drag formula:

\({C}_{Di} = \frac {{C_l} ^{2}} {pi \times AR \times e}\)

This scalar applies to the FLAP 0 configuration (in clean configuration, ie: no propeller, no turbulence, no engine wash, no gears, no flaps, no spoilers, no deflections...).

Default value is 1.

Float No
flap_induced_drag_scalar

Scales the induced drag target as defined by the target induced drag formula:

\({Cd}_{i} = \frac {Cl ^{2}} {pi \times AR \times e}\)

This scalar applies to the FULL FLAP configuration (ldg).

Default value is 1.

Float No
clcd_normalization_aoa_deg_low

Lower AoA at which the aircraft's lift & drag is normalised to the theory curve.

Default value is 0.

Float No
clcd_normalization_aoa_deg_high

Higher AoA at which the aircraft's lift & drag is normalized to the theory curve.

Default value is 12.4.

Float No
elevator_effectiveness

This scalar scales the elevator_lift_coef parameter in the [AERODYNAMICS] section.

Default value is 1.

Float No
elevator_maxangle_scalar

Scales the deflection angle of the elevator control surface up to the max deflection indicated in elevator_xxx_limit and already scaled by the elevator_elasticity_table.

The default value is 1.0, yet if the limit angles are matching the real aircraft, this scalar should be smaller than one as the effective deflection will be aligned with the overall htail and elevator chord. A value between 0.5 and 0.75 will work with most airplanes.

Float No
elevator_chordangle_scalar

Used to re-scale the elevator effectiveness using the following formula:

ratio = elevator_chordangle_scalar * elevator_area / (elevator_area + htail_area)

The ratio is then applied to the Clde, Cmde, CmdTrim and CmdePropwash.

Default value is -1.

Float No
aileron_effectiveness

Scales the elevator lift coefficient slope as defined in elevator_lift_coef in the [AERODYNAMICS] section. Increases or decreases elevator authority or "twitchyness" without affecting the deflection angle.

Default value is 1.

Float No
rudder_effectiveness

This scalar scales the rudder_lift_coef parameter in the [AERODYNAMICS] section. Values will increase or decrease lift authority or "twitchyness" without affecting the deflection angle.

Default value is 1.

Float No
rudder_maxangle_scalar

Scales the deflection angle of the rudder control surface up to the max deflection indicated in rudder_limit and already scaled by the rudder_elasticity_table.

The default value is 1, and if the limit angles are matching the real aircraft, this scalar should be less than 1 as the effective deflection will be aligned with the overall vtail and rudder chord. A value between 0.5 and 0.75 will work with most airplanes.

Float No
rudder_chordangle_scalar

Used to re-scale the rudder effectiveness using the following formula:

ratio = elevator_chordangle_scalar * elevator_area / (elevator_area + htail_area)

The ratio is then applied to the Cydr, Cldr, Cndr and CndrPropwash.

Default value is -1.

Float No
htail_maxangle_scalar

This scalar is used in the calculations that define the orientation of the elevator aerodynamic surfaces.

Default value is -1.

Float No
vtail_maxangle_scalar

This scalar is used in the calculations that define the orientation of the rudder aerodynamic surfaces.

Default value is -1.

Float No
pitch_stability

Sets a target value for aerodynamic resistance to pitch rotation for the plane. In the legacy flight model, this will scale the pitch_moment_pitch_damping variable. In the modern flight model, this will set a target aerodynamic resistance value that the flight model will try to reach by adding more rotation resistance to each surface. As this system can only add more resistance, there will be a minimum native aerodynamic resistance below which the system can't go. By setting a low target, such as 0.1, the target is usually below the native aerodynamic rotation resistance which means that this parameter will have no effect. To add more aerodynamic resistance, use larger values.

NOTE: Aerodynamic resistance to rotation is relative to the local air mass. If the local airmass is turbulent, increasing rotation resistance will make turbulence impact more on the aircraft.Default value is 1.

Float No
roll_stability

Sets a target value for aerodynamic resistance to roll rotation for the plane. In the legacy flight model, this will scale the roll_moment_roll_damping variable. In the modern flight model, this will set a target aerodynamic resistance value that the modern flight model will try to reach by adding more rotation resistance to each surface. As this system can only add more resistance, there will be a minimum native aerodynamic resistance below which the system can't go. By setting a low target, such as 0.1, the target is usually below the native aerodynamic rotation resistance which means that this parameter will have no effect. To add more aerodynamic resistance, use larger values.

NOTE: Aerodynamic resistance to rotation is relative to the local air mass. If the local airmass is turbulent, increasing rotation resistance will make turbulence impact more on the aircraft.Default value is 1.

Float No
yaw_stability

Sets a target value for aerodynamic resistance to yaw rotation for the plane. In the legacy flight model, this will scale the yaw_moment_yaw_damping variable. In the modern flight model, this will set a target aerodynamic resistance value that the modern flight model will try to reach by adding more rotation resistance to each surface. As this system can only add more resistance, there will be a minimum native aerodynamic resistance below which the system can't go. By setting a low target, such as 0.1, the target is usually below the native aerodynamic rotation resistance which means that this parameter will have no effect. To add more aerodynamic resistance, use larger values.

NOTE: Aerodynamic resistance to rotation is relative to the local air mass. If the local airmass is turbulent, increasing rotation resistance will make turbulence more impacting on the aircraft.Default value is 1.

Float No
pitch_gyro_stability

This variable controls pitch gyroscopic stability. Unlike aerodynamic stability - which is relative to the local airmass - gyroscopic stability is world relative and will not make the aircraft more sensitive to turbulence. It will have the opposite effect in reality: making the aircraft more stable relative to the world, it will become less sensitive to turbulent air. Gyroscopic stability in an aircraft is caused by turning parts such as the propellers or engine axis or turbines.

Default value is 0.

Float No
roll_gyro_stability

This variable controls roll gyroscopic stability. Unlike aerodynamic stability - which is relative to the local airmass - gyroscopic stability is world relative and will not make the aircraft more sensitive to turbulence. It will have the opposite effect in reality: making the aircraft more stable relative to the world, it will become less sensitive to turbulent air. Gyroscopic stability in an aircraft is caused by turning parts such as the propellers or engine axis or turbines.

Default value is 0.

Float No
yaw_gyro_stability

This variable controls yaw gyroscopic stability. Unlike aerodynamic stability - which is relative to the local airmass - gyroscopic stability is world relative and will not make the aircraft more sensitive to turbulence. It will have the opposite effect in reality: making the aircraft more stable relative to the world, it will become less sensitive to turbulent air. Gyroscopic stability in an aircraft is caused by turning parts such as the propellers or engine axis or turbines.

Default value is 0.

Float No
elevator_trim_effectiveness

Scales the elevator trim deflection angle and maximum trim deflection angle as defined in elevator_trim_limit.

Default value is 1.

Float No
aileron_trim_effectiveness

Scales the aileron trim deflection angle and maximum trim deflection angle.

Default value is 1.

Float No
rudder_trim_effectiveness

Scales the rudder trim deflection angle and maximum trim deflection angle as defined in rudder_trim_limit.

Default value is 1.

Float No
aileron_up_drag_scalar

Scales the drag added by upwards aileron deflection as defined in aileron_up_drag_coef parameter in the [AERODYNAMICS] section. This parameter has a significant impact on adverse yaw. Reduce upward deflection drag to get more adverse yaw.

Default value is 1.

Float No
aileron_down_drag_scalar

Scales the drag added by downwards aileron deflection as defined in aileron_down_drag_coef parameter in the [AERODYNAMICS] section. This parameter has a significant impact on adverse yaw. Increase downward deflection drag to get more adverse yaw.

Default value is 1.

Float No
hi_alpha_on_roll

Multiplier on the effects on roll at high angles of attack. This parameter is used in the legacy FSX flight model only to define the stall characteristics of the aircraft. It is not used anymore in the modern flight model.

The default value is 1.

Float No
hi_alpha_on_yaw

Multiplier on the effects on yaw at high angles of attack. This parameter is used in the legacy FSX flight model only to define the stall characteristics of the aircraft. It is not used anymore in the modern flight model.

The default value is 1.

Float No
p_factor_on_yaw

Scales the amount of p-factor induced yaw. P-factor is the result of the propeller providing asymmetric thrust when the propeller is not aligned with the trajectory.

The default value is 1.

Float No
torque_on_roll

Scales the amount of torque that is transmitted from the engine onto the aircraft. When the engine starts to roll into one direction, it will cause the aircraft to roll into the other direction.

The default value is 1.

Float No
gyro_precession_on_pitch

Scales the amount of gyroscopic precession the engine causes on the aircraft's pitch.

The default value is 1.

Float No
gyro_precession_on_yaw

Scales the amount of gyroscopic precession the engine causes on the aircraft's yaw.

The default value is 1.

Float No
engine_wash_on_roll

Scales the impact that the engine wash will have on the control surfaces of the aircraft that causes the aircraft to roll.

The default value is 0.

Float No
wing_engine_wash

Scales the amount of propeller wash that will affect the lift of the part of the wing right behind the propeller.

The default value is 1.

Float No
rudder_engine_wash_on_roll

Scales the amount of added rudder trim compensating engine wash impact on roll. This parameter is separated from the actual rudder trim because it will be disabled with the engine wash on roll depending on piloting assistance's.

The default value is 1.

Float No
wingflex_scalar

Wingflex is based on realistic lift force and gravity computations and default elasticity parameters for a standard wing. This scalar allows to scale the amount of wingflex written to the WING_FLEX_PCT SimVar.

Default value is 1.

Float No
wingflex_surface_scalar

This scalar can be used to modify how the actual aerodynamic surfaces are being flexed by the wingflex force. Set to 1, it should approximately do the correct wingflex, but it will depend on the aircraft wing stiffness.

Default value is 0.

Float No
wingflex_offset Wingflex is based on realistic lift force and gravity computations and default elasticity parameters for a standard wing. This offset allows to offset the amount of wingflex written to the WING_FLEX_PCT SimVar.

Default value is 0.

Float No
stallpitchscalar

This parameter cuts off some of the stalling ability in the modern flight model. In general we don't recommend using anything other than the default value for this parameter, except for aircraft that can fly at extreme AoAs, like delta-wings, for example.

Default value is 1.

Float No
predicted_moi_density_scalar_fuselage

In the Weight debug window, this parameter will impact the predicted MOI that is displayed and can be used to help configure the MOI.

IMPORTANT! This parameter is provided for debug information only and editing it will not affect the flight model.

Default value is 1.

Float No
predicted_moi_density_scalar_wings

In the Weight debug window, this parameter will impact the predicted MOI that is displayed and can be used to help configure the MOI.

IMPORTANT! This parameter is provided for debug information only and editing it will not affect the flight model.

Default value is 1.

Float No
disable_assistances

When set to 1 (TRUE) this will disable all available assistance for the aircraft.

Default value is 0 (FALSE).

Bool No
prop_moment_transfer_on_roll

This parameter allows you to scale how much of the propeller acceleration moment is transferred back to the aircraft body. Note that this does not apply to the absorbed torque, only to the RPM acceleration moment.

Default value is 0.

Float No
ground_crosswind_effect_zero_speed

This parameter represents the world speed (in ft per second) at which 0% of the crosswind effect is applied to the aircraft. This parameter will work in two different ways:

  • With the ground rudder assistance enabled, at the given speed and below, the lateral (x) component of the wind is set to zero.
  • With the ground rudder assistance disabled, crosswind is completely cancelled out below ground_crosswind_effect_zero_speed ft per seconds of IAS, and it is gradually blended in up to 100% at ground_crosswind_effect_max_speed ft per seconds of IAS.

Note that this value can be set to -1000 to have a 100% realistic simulation where the crosswind is never cancelled out.

Default value is 5.

Float No
ground_crosswind_effect_max_speed

This parameter represents the world speed (in ft per second) at which 100% of the crosswind effect is applied to the aircraft.

Note that this value can be set to -1000 to have a 100% realistic simulation where the crosswind is never cancelled out.

Default value is 80.

Float No
ground_high_speed_steeringwheel_static_friction_scalar

At high speeds, tires are rolling and - depending on their shape and width and how much they are inflated - they will more or less resist rotation or sideways motion. This parameter allows you to define how much a movable wheel resists static friction which goes sideways or resists rotation around the vertical axis. Essentially, it allows you to control how much the aircraft will move into the crosswind when rolling at higher speeds, and reducing the scalar will reduce the friction, so the aircraft is more likely to slide. Note that only the lateral forces are impacted by this value, so rolling friction and braking when your aircraft is rolling straight will not be influenced.

Default value is 1.

Float No

ground_high_speed_otherwheel_static_friction_scalar

At high speeds, tires are rolling and - depending on their shape and width and how much they are inflated - they will more or less resist rotation or sideways motion. This parameter allows you to define how much a non-movable wheel resists static friction which goes sideways or resists rotation around the vertical axis. Essentially, it allows you to control how much the aircraft will move into the crosswind when rolling at higher speeds, and reducing the scalar will reduce the friction, so the aircraft is more likely to slide. Note that only the lateral forces are impacted by this value, so rolling friction and braking when your aircraft is rolling straight will not be influenced.

Default value is 1.

Float No
stall_coef_at_min_weight

This coefficient is used as part of the calculations involved with defining the predicted stall speed that will be used to guide the auto-pilot and FBW systems. The actual calculation is as follows:

stallSpeed = flapStallSpeed * (stall_coef_at_min_weight + (1 - stall_coef_at_min_weight) * weightPercent)

Default value is 0.5.

Float No
ground_new_contact_model_gear_flex

This defines the added compliance (ie: the inverse of the "stiffness") of the landing gears when the soft contact simulation physics is active. It is measured in ft per pound of force.

For more information, please see the Note On Ground Contact Model.

Default value is 0.0

Float No
ground_new_contact_model_gear_flex_damping

This defines the added damping (energy dispersion in heat) of the landing gears with the new soft contact simulation physics enabled. It is measured in lbs per ft per second.

For more information, please see the Note On Ground Contact Model.

Default value is 0.0

Float No
ground_new_contact_model_rolling_stickyness

This can be used to further reduce the sideways friction on wheels due to the effects of the rolling wheel. Value is expressed as a ratio where 1 is no effect.

For more information, please see the Note On Ground Contact Model.

Default value is 1

Float No
ground_new_contact_model_up_to_speed_lateral

This defines the lateral speed, in ft per second, up to which the new contact model will be used for all non-steering wheels. Speeds greater than this will revert to the legacy contact model.

For more information, please see the Note On Ground Contact Model.

Default value is 0.1

Float No
ground_new_contact_model_up_to_speed_lateral_steering

This defines the lateral speed, in ft per second, up to which the new contact model will be used on all steering wheels only. Speeds greater than this will revert to the legacy contact model.

For more information, please see the Note On Ground Contact Model.

Default value is 0.1

Float No
ground_new_contact_model_up_to_speed_longitudinal

This defines the longitudinal speed, in ft per second, up to which the new contact model will be used. Speeds greater than this will revert to the legacy contact model.

For more information, please see the Note On Ground Contact Model.

Default value is 1.0

Float No
enable_high_accuracy_integration

This option enables the high accuracy world physics integration for the aircraft. When enabled, the simulation will take into account multiple sources of physics interactions that create oscillating/vibrating micro-movements in the aircraft, for example engine shaking, wind resonance, etc... when the aircraft is on the ground. If this is disabled, then these micro-movements are not accounted for.

For more information, please see the Note On Ground Contact Model.

Default value is 0

Float No

 

 

[REFERENCE SPEEDS]

This section contains various reference speed values used in different systems across the sim like the Flight Assistant, the Aircraft Selection UI, notifications, or overspeed triggers. Most of these parameters will have no direct effect on the flight model.

 

The available parameters are:

 

Parameter Description Type Required
full_flaps_stall_speed

Speed at which the aircraft will stall when flaps are at full, in kias. Used in the Flight Assistant.

Default value is 0.

Float No
flaps_up_stall_speed

Speed at which the aircraft will stall when flaps are up, in kias. Used in the Flight Assistant.

Default value is 0.

Float No
cruise_speed

The aircraft cruise speed, in ktas. Used in aircraft selection UI

Default value is 0.

NOTE: For gliders, this value will also affect the launch winch speed. The winch will accelerate at 1G until the aircraft reaches 75% of the design cruise speed, and then progressively reduce power once the glider has passed 30°.

Float No
cruise_mach

The aircraft cruise speed, in Mach.

Default value is 0.

Float No
crossover_speed

The aircraft crossover speed, in kias.

Default value is 0.

Float No
max_mach

The maximum speed for the aircraft, in Mach. Used in aircraft selection UI.

NOTE: Only valid for Jet and Turboprop engines.

Default value is 0.9.

Float No
max_indicated_speed

The maximum speed indicated in the aircraft UI, in kias.

Default value is 0.

Float No
max_flaps_extended

The maximum aircraft speed with flaps extended, in kias. Used in the Flight Assistant.

Default value is 0.

Float No
normal_operating_speed

The normal operating speed of the aircraft, in kias. Used in aircraft selection UI.

Default value is 0.

Float No
airspeed_indicator_max

The maximum airspeed indicator value in the UI, in kias.

Default value is 0.

Float No
rotation_speed_min

The minimum rotation speed required, in Knots.

Default value is -1.

Float No
climb_speed

The aircraft climb speed, in Knots. Used to define spawning conditions.

Default value is 0.

Float No
cruise_alt

The aircraft cruise altitude, in ft.

Default value is 1500.

Float No
takeoff_speed

The aircraft takeoff speed, in Knots.

Default value is 55.

Float No
spawn_altitude

The spawn altitude, in ft.

Default value is 1500.

 

Float No
spawn_cruise_altitude

The spawn cruise altitude, in ft. Used to define spawning conditions.

Default value is 1500.

Float No
spawn_descent_altitude

The spawn descent altitude, in ft. Used to define spawning conditions.

Default value is 500.

Float No
best_angle_climb_speed

The best angle climb speed, in Knots.

Default value is 0.

Float No
approach_speed

The required approach speed, in Knots.

Default value is 0.

Float No
best_glide

The best glide speed, in Knots.

Default value is 0.

Float No
max_gear_extended

The maximum speed with landing gear extended, in Knots.

Default value is 0.

Float No
best_single_engine_rate_of_climb_speed

This is the best single-engine rate of climb speed (the Blue line speed, \(V_{yse}\) ), in Knots.

Default value is 0.

Float No
minimum_control_speed

This is the speed below which aircraft control cannot be maintained if the critical engine fails under a specific set of circumstances (generally known as the \(V_{mc}\) ). Value is in Knots.

Default value is 0.

Float No
fly_assistant_use_dynamic_speeds

This parameter refers to how the UI will display the relevant reference speeds for takeoff, climb, etc... When set to 1 (TRUE), the values will by dynamically generated by the simulation, and when set to 0 (FALSE) the values in the CFG file will be used. Note that this has no effect on the flight model.

Default is 0 (FALSE).

Bool No

 

 

[STALL PROTECTION]

Stall protection is a system which prevents the AoA from getting too high. This is done by software monitoring the plane's angle of attack sensor, and when a high alpha situation is detected, the software lowers the nose of the plane to maintain a high - but still safe - AoA. This system is designed to prevent pilots from stalling the aircraft and to allow them to get the best possible performance in emergency e.g. in a wind-shear.

NOTE: This section is required when the fly_by_wire parameter is checked for active stall protection. However if fly_by_wire is not checked, the values here will still be used to generate the simulation stall warnings.

NOTE: This section is not required if you are creating a Helicopter SimObject.

The following parameters can be used to control this system:

 

Parameter Description Type Required
stall_protection

Whether Stall Protection is enabled (TRUE, 1) or not (FALSE, 0).

Default is 0.

Bool No
off_limit

Alpha below which the Stall Protection can be disabled, in degrees (if also below off_yoke_limit).

Default is 0.

Float
off_yoke_limit

Yoke position percentage below which the Stall Protection can be disabled (if also below off_limit).

Default is 0.

Float
on_limit

Alpha - in degrees - above which the Stall Protection timer starts.

Default is 0.

Float
on_goal

The alpha - in degrees - that the Stall Protection will attempt to reach when triggered.

Default is 0.

Float
timer_trigger

Duration, in seconds, that the alpha must be above on_limit before the Alpha Protection is triggered.

Default is 0.

Float

 

 

[FLAPS.N]

This section is for tuning the different flaps for the aircraft. You can have multiple [FLAPS.N] sections where N relates to the flap being defined from 0 up to the number of flaps - 1. For example, if you have two flaps you would have two sections, [FLAPS.0] and [FLAPS.1].

NOTE: This section is not required if you are creating a Helicopter SimObject.

 

The available parameters are:

 

Parameter Description Type Required
type

Defines the flaps type.

Integer:

  1. 0 = none
  2. 1 = trailing edge
  3. 2 = leading edge
Yes
system_type Defines the type of electrical system that drives the flaps to deflect.

Integer:

  1. 0 = electrical
  2. 1 = hydraulic
  3. 2 = pneumatic
  4. 3 = manual
  5. 4 = none
Yes
system_type_index

If using electrical flaps, this parameter specifies the index of the flaps motor circuit.

Default is 0.

Integer No
span-outboard

Outboard span area, as a Percent Over 100 This is how far out from the wing-root that the flaps stretch (the total span is considered as the distance between wing root and wing tip). On most planes this will be 1.0 - aileron_span_outboard. This value needs to be matching the lift and drag added by flaps. Small flap systems should add small amounts of lift.

Default value is 0.75, and note that any input value given is clamped between 0.4 and 1.0.

IMPORTANT! Despite the flaps span being defined in each flap section, the span is common to all the simulation will take the maximum span value defined in flap sections and clamp it between 0.4 and 1.0

Float No
extending-time

Time it takes for the flap set to extend to the fullest deflection angle specified (in seconds).

Default value is 0.

Float No
flaps-sequence-increasing

If set, this specifies that these flaps should only start moving towards the down position when the flaps with the corresponding index have finished moving.

Default is -1, which means no such restriction should be applied.

Integer No
flaps-sequence-decreasing

If set, this specifies that these flaps should only start moving towards the up position when the flaps with the corresponding index have finished moving.

Default is -1, which means no such restriction should be applied.

Integer No
damaging-speed

Speed above which the flaps begins to get damaged, if extended, in Knots. For more information please see here: Flaps Damage and Blowout.

Default value is 0, which means no damage will be applied, regardless of the speed.

Float No
blowout-speed

Speed above which the flaps are blown out, in Knots. For more information please see here: Flaps Damage and Blowout.

Default value is 0, which means no blowouts will occur, regardless of the speed.

Float No
maneuvering_flaps

Sets whether maneuvering flaps are available (TRUE, 1) or not (FALSE, 0).

Default value is 0 (FALSE).

Bool No
delay_between_flap_index

 

Default value is 0.

Float No
lift_scalar

Scalar that allows you to scale the lift contribution of a specific flap system. This is necessary to compensate for the scale by the deflection angle in radians, in order to reach 100%, ie: the computed lift coefficient is multiplied by the surface deflection, so you need to compensate for this deflection if it's inferior to 1 radian to reach 100% of your lift coefficient.
The flap lift formula is the following:

total_flap_lift = lift_coef_flaps * (system1.lift_scalar * system1.deflectionangleradians + system2.lift_scalar * system 2.deflectionangleradians...)

Default value is 1.

Float No
drag_scalar

Scalar that allows you to scale the drag contribution of a specific flap system. It is necessary to compensate for the scale by the deflection angle in radians, in order to reach 100%, ie: the computed drag coefficient is multiplied by the surface deflection, so you need to compensate for this deflection if it's inferior to 1 radian to reach 100% of your drag coefficient.
The flap drag formula is the following:

total_flap_drag = drag_coef_flaps * (system1.drag_scalar * system1.deflectionangleradians + system2.drag_scalar * system 2.deflectionangleradians...)

Default value is 1.

Float No
pitch_scalar

The percentage of total pitch due to flap deflection that this flap set is responsible for at full deflection.

This is a legacy FSX parameter not used in the modern flight model. In the modern flight model, the pitch generated by flaps will depend on the lift added and the longitudinal position of the wings. The parameters of each flap level allow to move the wing longitudinally for each flap level to adjust the amount of pitch.

Default value is 1.

Float No
max_on_ground_position The maximal flap extension stage available when an aircraft is on the ground. This must be a value between 0 and the maximal stage described (see flaps-position.N). Integer No
altitude-limit

Specifies an altitude (in ft) above which the flaps cannot be extended.

Default is -1, which disables the feature.

Float No
FlapSurface_Left

This parameter provides one or more references to a damage profile that has been defined in the [COLLISION_DAMAGE] section of the flight model CFG file, and will be used to gauge the quantity of damage applied to the left flaps surfaces.

The information is given as a hash map with the key WearAndTearCollision, which will take a sting reference to a damage profile. For example:

FlapSurface_Left = WearAndTearCollision:LeftWingLight

For more information, please see here: Note On Collision Damage / Wear And Tear

Hash Map

No
FlapSurface_Right This parameter provides one or more references to a damage profile that has been defined in the [COLLISION_DAMAGE] section of the flight model CFG file, and will be used to gauge the quantity of damage applied to the right flaps surfaces.

The information is given as a hash map with the key WearAndTearCollision, which will take a sting reference to a damage profile. For example:

FlapSurface_Right = WearAndTearCollision:LeftWingRight

For more information, please see here: Note On Collision Damage / Wear And Tear

Hash Map

No
FlapCable_Left This parameter provides one or more references to a damage profile that has been defined in the [COLLISION_DAMAGE] section of the flight model CFG file, and will be used to gauge the quantity of damage applied to the left flaps control cable.

The information is given as a hash map with the key WearAndTearCollision, which will take a sting reference to a damage profile. For example:

FlapCable_Left = WearAndTearCollision:LeftWingHeavy

For more information, please see here: Note On Collision Damage / Wear And Tear

Hash Map

No
FlapCable_Right This parameter provides one or more references to a damage profile that has been defined in the [COLLISION_DAMAGE] section of the flight model CFG file, and will be used to gauge the quantity of damage applied to the right flaps control cable.

The information is given as a hash map with the key WearAndTearCollision, which will take a sting reference to a damage profile. For example:

FlapCable_Right = WearAndTearCollision:RightWingHeavy

For more information, please see here: Note On Collision Damage / Wear And Tear

Hash Map

No
flaps-position.i

This is a flap stage description, and you can have multiple definitions (starting at flaps-position.0) for each [FLAPS.N] section. The table of values takes the following 7 values in the given order:

  • flap position - sets the flaps angular position for the stage, in degrees.
  • airspeed limit - sets the airspeed limit for the stage, in Knots.
  • drag scalar - sets a scalar to add or remove drag for the stage.
  • lift scalar - sets a scalar to add or remove lift for the stage.
  • area scalar - sets a scalar to add or remove area to the flap for the stage.
  • add camber - sets an increase in the flap camber, raising the maximum lift coefficient or the upper limit to the lift a wing can generate. The value here is expressed in radians.
  • add aft feet - sets the center of lift for the flaps stage, where a positive value will move the center of lift forward (generating more pitch up) and a negative value will move it back (generating more pitch down).
  • add incidence - a scalar that lets you define how much of the additional lift is applied at 0° AoA. So, when set to 1 (100%), the additional lift is added constantly on the whole AoA range. When set to 0.5 (the default value), only 50% of the additional lift will be added at 0° of AoA and 100% at the stall AoA. The values in between depend on the normalization process.
    0.5 (50%) is the minimal value and you can go beyond 1.0, if required.

List of Floats

Yes

flaps-position-inhibit-or.i

Alias :

flaps-position-inhibit.i

This is a comma separated table of conditions which - if any of them are valid - will inhibit the flaps settings from affecting the flaps at position i. There can be multiple entries for this parameter, one for each flaps position, with i starting at 0 and up to number of positions - 1. Can be any of the following:

  1. "air" - plane is in the air
  2. "ground" - plane is on the ground
  3. "increasing" - inhibit only if rising flaps level
  4. "decreasing" - inhibit only if decreasing flaps level

By default this is set to "", "", "", "".

List of Strings

No
flaps-position-inhibit-and.i

This is a coma separated table of conditions which - if all of them are valid - will inhibit the flaps settings from affecting the flaps at position i. There can be multiple entries for this parameter, one for each flaps position, with i starting at 0 and up to number of positions - 1. Can be any of the following:

  1. "air" - plane is in the air
  2. "ground" - plane is on the ground
  3. "increasing" - inhibit only if rising flaps level
  4. "decreasing" - inhibit only if decreasing flaps level

By default this is set to "", "", "", "".

List of Strings

No
flaps-position-autoretract.i

This parameter sets the auto-retract rules for flaps. There can be multiple entries for this parameter, one for each flaps position, with i starting at 0 and up to number of positions - 1. The parameter requires a comma separated table of values in the following order:

  1. - the flaps angle in degrees
  2. - the airspeed in Knots at which the auto-retract triggers
  3. - the new airspeed limit, in Knots

List of Floats

Yes
flaps-position-maneuvering.i

When set to 1 (TRUE) flaps position i will have a dynamic maneuvering flaps behavior rather than a static degree value. Set to 0 (FALSE) to disable this feature for the flaps. There can be multiple entries for this parameter, one for each flaps position, with i starting at 0 and up to number of positions - 1.

Boolean No
flaps-position-speed-factor.i

This parameter requires a table of values that set the correspondence between the speed (in Knots) of the plane and a factor (from 0 - 1) on the max angle of the flaps position i. For example:

flaps-position-speed-factor.0 = 0:1, 150:1, 240:0 ;

Here, between 0 and 150 you get the full flaps position, but above 150 it starts getting reduced linearly until 240 at which point it's 0.

There can be multiple entries for this parameter, one for each flaps position, with i starting at 0 and up to number of positions - 1.

1D Curve of Floats

No
flaps-position-speed-override-above.i

This parameter sets the override rules for flaps at the given position when above a certain speed. There can be multiple entries for this parameter, one for each flaps position, with i starting at 0 and up to number of positions - 1. The parameter requires the following two values, separated by a comma:

  • the flaps position to use as the override
  • the speed (in Knots) above which the given flaps position is used instead of the current one.

List of Floats

No
flaps-position-speed-override-below.i

This parameter sets the override rules for flaps at the given position when below a certain speed. There can be multiple entries for this parameter, one for each flaps position, with i starting at 0 and up to number of positions - 1. The parameter requires the following two values, separated by a comma:

  • the flaps position to use as the override
  • the speed (in Knots) below which the given flaps position is used instead of the current one.

List of Floats

No

 

 

[DESIGN_ACTIVATION]

The flight model in Microsoft Flight Simulator 2024 permits more granularity when it comes to creating the features of an aircraft. This granularity starts in this section, where you can select specific parts of the "standard" flight model to activate or deactivate, and then continue on to define your own sections for the deactivated parts. For example, it may be that you want to have more control over how the aircraft fuselage is created, since the standard simulation fuselage is low detail, always centered and there are not a lot of ways to control the shape. So you may have something like this in this section:

[DESIGN_ACTIVATION]
enable_aircraft_geometry_vtail = 1
enable_aircraft_geometry_htail = 1
enable_aircraft_geometry_fuselage = 0
enable_aircraft_geometry_wing = 1
enable_aircraft_geometry_gears = 1
enable_aircraft_geometry_exttank = 1
enable_aircraft_geometry_blades = 1

 

This tells the simulation that you do not wish to use the standard fuselage definition, and will be adding in an [OBJ_EA1_FUSELAGE.N] section with the details of the more advanced custom fuselage (note that you may add in multiple sections if, for example, the aircraft has a dual fuselage like the F-82 Twin Mustang).

 

The parameters available in this section are as follows:

 

Parameter Description Type Required
enable_aircraft_geometry_vtail

This is used to enable (1) or disable (0) the standard Vertical Tail geometry for the aircraft.

Default value is 1.

Bool No
enable_aircraft_geometry_htail

This is used to enable (1) or disable (0) the standard Horizontal Tail geometry for the aircraft.

Default value is 1.

Bool No
enable_aircraft_geometry_fuselage

This is used to enable (1) or disable (0) the standard fuselage geometry for the aircraft.

Default value is 1.

Bool No
enable_aircraft_geometry_wing

This is used to enable (1) or disable (0) the standard wing geometry for the aircraft.

Default value is 1.

Bool No
enable_aircraft_geometry_gears

This is used to enable (1) or disable (0) the standard landing gear geometry for the aircraft.

Default value is 1.

Bool No
enable_aircraft_geometry_exttank

This is used to enable (1) or disable (0) the standard external tank geometry for the aircraft.

Default value is 1.

Bool No
enable_aircraft_geometry_blades

This is used to enable (1) or disable (0) the standard rotor blade geometry for the aircraft.

Default value is 1.

Bool No

 

 

[OBJ_EA1_FUSELAGE.N]

COMING SOON!

 

 

[OBJ_EA1_SURFACE.N]

COMING SOON!

 

 

[OBJ_EA1_BALLOON.N]

COMING SOON!

 

 

[OBJ_EA1_ANCHORROPE.N]

COMING SOON!

 

 

[OBJ_EA1_PITOTFLAG.N]

THis is used to define a physics object that is used to display the "Remove Before Flight" warning hanging from many of the preflight check items. You can have multiple of these sections where the appended number N corresponds to its unique ID (starting at 0, and incrementing by 1 for each flag that you wish to add). Full instructions on setting up this item are given on the following page:

 

The parameters available in this section are as follows:

 

Parameter Description Type Required
position This is the position of the object relative to the Datum Reference Point, expressed as X, Y, Z values, in ft. This is the point where the flag will be attached to the protective cover object. List of Floats Yes
size This is used to define the size of the flag that will display the warning text. The size is expressed in meters as width, length, thickness. Note that thickness should be 0 and is not used by this object. List of Floats Yes
linked_behavior_index This defines the interaction that is to be used for the flag. Since the flag can be attached to various different protective covers, you need to specify the behavior to use when the cover is removed so that it matches the cover type.

Enum:

  1. 1: Engine Cover
  2. 2: Pitot Cover
  3. 3: Static Cover
  4. 5: Gear Pin
  5. 6: Propeller Cover or Rotor Cover
Yes
surface_relative_position

The warning flag object is is created with physical properties which means that it will move around based on the wind and airflow around the aircraft. To prevent the object "clipping" into anything it shouldn't this parameter is used to set the relative position of the nearest collision surface. For example, you may have this flag on a static cover on the aircraft fuselage, and since it should not pass through the airframe model, you would set the position of the collision surface to be where the fuselage is.

This surface plane position is relative to the position of the flag, expressed as X, Y, Z values, in ft.

List of Floats Yes
surface_angle This sets the angle of the collision surface at the position defined by the surface_relative_position. This angle is expressed as three values (in degrees): pitch, bank, and heading. List of Floats Yes
material_guid

Here you give the unique GUID of the material to use for the warning flag. For consistency, we recommend that you use the default Microsoft Flight Simulator 2024 material which has the following GUID:

E48F59B9-94E0-4CA2-B261-8E5FFFF3CB03

String Yes

 

 

[OBJ_EA1_YAWSTRING.N]

COMING SOON!

 

 

[OBJ_EA1_ROPECRATE.N]

COMING SOON!

 

 

[OBJ_EA1_BANNER.N]

COMING SOON!

 

 

[OBJ_EA1_SIMPLEGEAR.N]

COMING SOON!

 

 

[INTERACTIVE POINTS]

Interactive Points in Microsoft Flight Simulator 2024 are used to define the position of various doors of the aircraft - regular, emergency, and cargo doors - as well as some other points to interact with Apron Services, such as the end of a fuel hose to interact with a FuelTruck, or the end of an electrical cable to interact with a GroundPowerUnit vehicle. Interactive points should be added through the SimObject Editor, and only tweaked if required through the flight_model.cfg file.

NOTE: While interactive points are currently stored in the flight_model.cfg file, they have no relationship with the actual Flight Model for an aircraft. Future updates to the SDK may move this data to another file.

 

The [INTERACTIVE POINTS] section should contain one or more interactive_point.i = <DATA> definitions, where i is a value between 0 and N - 1. , and <DATA> is a list of values that set up the interactive point. Below you can see an example of interactive points being defined:

[INTERACTIVE POINTS]
interactive_point.0 = Name:pDoorFrontL #Properties: 0.4, 27.93, -6.05, 3.02, 0, 0, 0, -86, 72, 16, 85, 3, -2, 33, -1
interactive_point.1 = Name:pDoorFrontR #Properties: 0.4, 27.93, 6.05, 3.02, 0, 0, 0, 86, 85, 3, 72, 16, -2, 33, -1
interactive_point.2 = Name:pDoorCentreL #Properties: 0.4, -53, -5.2, 3, 0, 0, 0, -103, 0, 0, 0, 0, 0, 0, -1
interactive_point.3 = Name:pDoorCentreR #Properties: 0.4, -53, 5.2, 3, 0, 0, 0, 103, 0, 0, 0, 0, 0, 0, -1
interactive_point.4 = Name:pDoorBackL #Properties: 0.4, -29.5, 2, -1.8, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0, -1
interactive_point.5 = Name:pDoorBackR #Properties: 0.4, 18, 1.93, -1.9, 1, 0, 0, 90, 0, 0, 0, 0, 0, 0, -1
interactive_point.6 = Name:pEmergencyL #Properties: 0.4, -4, -6, 6.2, 2, 0, 0, -90, 0, 0, 0, 0, 0, 0, -1
interactive_point.7 = Name:pEmergencyR #Properties: 0.4, -4, 6, 6.2, 2, 0, 0, 90, 0, 0, 0, 0, 0, 0, -1
interactive_point.8 = Name:pCargo1 #Properties: 0, 36.3, 10.78, -5.18, 4, 0, 0, 45, 0, 0, 0, 0, 0, 0, -1
interactive_point.9 = Name:pCargo2 #Properties: 0, 0, -54.59, -7.57, 3, 0, 0, -90, 0, 0, 0, 0, 0, 0, -1

The available parameters for the [INTERACTIVE POINTS] section are:

 

Parameter Description Type Required
interactive_point.N

A hash map that defines the name and properties of an interactive point.

Hash Map

No

 

Each interactive point definition requires a hash map with the following keys:

 

Key Value Description Required
Name String This is a name string that is used as an alias to identify the interactive point. It will also be used as the reference index for SimVars, and note that the name is the only guaranteed reference to the component due to the fact that the Modular Aircraft Merging process may change the index. The name cannot contain special characters or spaces. Yes
Properties List

List that contains all the information about the interactive point.

Yes

 

 

For the properties, you need to supply a list of 15 different values. The table below explains what each one of the values represents, as well as the Interactive Points SimVar associated with it (if it has one):

 

Position Position Name Description Type SimVar
0 Open Close Rate Percent Over 100 per second of animation of the interactive point (used mostly for doors). Float
  1. -
1 Pos - Z Coordinate in ft of the point relative to aircraft , on the back-to-front (Z) axis. Float
  1. INTERACTIVE POINT POSZ
2 Pos - X Coordinate in ft of the point relative to aircraft , on the left-to-right (X) axis. Float
  1. INTERACTIVE POINT POSX
3 Pos - Y Coordinate in ft of the point relative to aircraft , on the bottom-to-top (Y) axis. Float
  1. INTERACTIVE POINT POSZ
4 Type Integer corresponding to an enum, determining the type of the point (see the Type, Position, and Orientation section for more details).

Integer:

  1. 0 = Main exit
  2. 1 = Cargo exit/door
  3. 2 = Emergency exit
  4. 3 = Fuel hose
  5. 4 = Ground Power cable
  6. 5 = Air Start Unit
  7. 6 = Tailhook
  8. 7 = Drop Exit (for skydiving)
  9. 8 = Window
  10. 99 = Unknown (used for errors)
  1. INTERACTIVE_POINT_TYPE
5 Orientation - Pitch Pitch, in degrees, of the point orientation, where 0° means horizontal. Float
  1. INTERACTIVE POINT PITCH
6 Orientation - Bank Bank, in degrees, of the point orientation (currently unused, please set 0 here). Float
  1. INTERACTIVE POINT BANK
7 Orientation - Heading Heading, in degrees, of the point orientation (0° means same heading as the aircraft). Float
  1. INTERACTIVE POINT HEADING
8 Jetway Left Bend A percentage value for the jetway left bend. See the Jetway Values section for more information. Float
  1. INTERACTIVE POINT JETWAY LEFT BEND
9 Jetway Left Deployment A value, in degrees, for the jetway left deployment. See the Jetway Values section for more information. Float
  1. INTERACTIVE POINT JETWAY LEFT DEPLOYMENT
10 Jetway Right Bend A percentage value for the jetway right bend. See the Jetway Values section for more information. Float
  1. INTERACTIVE POINT JETWAY RIGHT BEND
11 Jetway Right Deployment A value, in degrees, for the jetway right deployment. See the Jetway Values section for more information. Float
  1. INTERACTIVE POINT JETWAY RIGHT DEPLOYMENT
12 Jetway Top Horizontal A value, between -100 and 100, for the jetway horizontal line. See the Jetway Values section for more information. Float
  1. INTERACTIVE POINT JETWAY TOP HORIZONTAL
13 Jetway Top Vertical A value, between -100 and 100, for the jetway vertical line. See the Jetway Values section for more information. Float
  1. INTERACTIVE POINT JETWAY TOP VERTICAL
14 Exit Open Failure Speed A value which corresponds to the speed at which the aircraft will have a failure if an exit is open, in ft per second. This is only valid if the interactive point is of the type 0 (Exit). If set to -1, failures of this type will be disabled, and if not included then the default speed is 50 ft per second Float -

 

 

[yaw_string]

This section is for setting up a yaw string on the aircraft. The available parameter is:

 

Parameter Description Type Required
yaw_string_available

Sets whether the simulation should generate the appropriate values for a yaw-string or not. Enabling this does nothing visually, but enables the SimVars YAW STRING ANGLE and YAW STRING PCT EXTENDED which can then be used to animate a yaw-string model.

For yaw-strings in Microsoft Flight Simulator 2024 please see: [OBJ_EA1_YAWSTRING.N]

Boolean No

 

 

[HELICOPTER]

This section is for setting up the various helicopter-specific components of the flight model. If you are modelling a helicopter then this section is essential, and is used - along with the [FUSELAGE_AERODYNAMICS], [MAINROTOR] and [SECONDARYROTOR] sections - to define the flight model, and including these sections usually means there is no need to include data for the [FLIGHT_TUNING], [AERODYNAMICS] and [AIRPLANE_GEOMETRY] sections. It is worth noting, however, that you will need to set up the [TURBOPROP_ENGINE] and [TURBINEENGINEDATA] sections (those that are not flagged as "jet only") of the engines.cfg file as well.

 

The available parameters are:

 

Parameter Description Type Required
enable_custom_throttles_control

When this parameter is set to 1 (TRUE) you may control the engine throttles directly using the appropriate SimVars, therefor bypassing (essentially disabling) the default internal simulation functionality.

Default value is 0 (FALSE).

Bool No
reference_length The overall length of the helicopter fuselage (excluding rotors), in ft. Float Yes
reference_frontal_area The front facing area of the helicopter fuselage (excluding rotors), in sqft. Float Yes
reference_side_area The lateral facing area of the helicopter fuselage (excluding rotors), in sqft. Float Yes
right_trim_scalar

This value scales the lateral cyclic trim position.

Default value is 1.

Float No
front_trim_scalar

This value scales the longitudinal cyclic trim position.

Default value is 1.

Float No
right_trim_step

The right trim increment value.

Default value is 0.005.

Float No
front_trim_step

The front trim increment value.

Default value is 0.005.

Float No
governed_pct_rpm_ref

This is the ratio of the rated RPM that the rotor RPM governor will try to achieve, expressed as a Percent Over 100.

Default value is 1.

Float No
governed_pct_rpm_min

This is the ratio of the rated RPM above which the governor will be enabled, expressed as a Percent Over 100. Note that this value must be positive and negative values will be clamped at 0.

Default value is 0.

Float No
governor_speed_limit

This sets the limit on the maximum speed of throttle movement by the governor. The value given here is a a ratio between 0 and 1, where the limit is calculated as ratio / sec. If set to 0, then there is no limit imposed.

Default value is 1.

Float No
rotor_brake_scalar

With this parameter you can scale the rotor braking torque.

Default value is 1.

Float No
rotor_brake_torque

This value adjusts the rotor braking torque. The value is in ftlbs per ft.

Default value is 600.

Float No
rotor_brake_bleed_rate

This defines the decay per second (as a Percent Over 100) of the brake type. Value must be be greater or equal to 0

Default value is 0.5.

Float No
rotor_friction_torque

This value adjusts the speed at which the rotors will slow down after shutting off the engine. The value is in ftlbs per ft.

Default value is 0.

Float No
rotor_node.n

This parameter is used to give the nodes for the center of each rotor, where n increments by 1 for each engine with a node. This will be used to generate the blurring effect when the rotor is spinning. For example:

rotor_node.0 = NODES:rotor_L
rotor_node.1 = NODES:rotor_R

It is also possible to configure more than one node per engine (this allows to have 2 versions of a rotor with low or high detail), for example:

rotor_node.0 = NODES:rotor_L, rotor_L_blur
rotor_node.1 = NODES:rotor_R, rotor_R_blur

If the node is not part of the base model in a modular SimObject, then you can also supply an alias which is used in the merge process to ensure the correct node is selected, for example:

rotor_node.0 = SimAttachmentAlias:Exterior # Nodes:rotor_L
rotor_node.1 = SimAttachmentAlias:Exterior # Nodes:rotor_R

Hash Map

No
torque_scalar

With this parameter you can scale the rotor torque effect. NOTE: This parameter will only be used when the use_modern_surfaces parameter is set to 0.Default value is 1.

Float No
tail_rotor_translating_scalar

This parameter scales the tail rotor thrust.NOTE: This parameter will only be used when the use_modern_surfaces parameter is set to 0.Default value is 1.

Float No
disk_roll_animation_scalar

This parameter scales the rotor disk roll animation angle.

Default value is 1.

Float No
disk_pitch_animation_scalar

This parameter scales the rotor disk pitch animation angle.

Default value is 1.

Float No
cyclic_roll_control_scalar

This parameter scales the roll cyclic controls. Note that this will be applied to both the positive and negative input, unless cyclic_roll_control_scalar_negative is defined.

Default value is 1.

Float No
cyclic_roll_control_scalar_negative

This parameter scales the roll cyclic controls.

Default value is 1.

Float No
cyclic_pitch_control_scalar

This parameter scales the pitch cyclic controls. Note that this will be applied to both the positive and negative input, unless cyclic_pitch_control_scalar_negative is defined.

Default value is 1.

Float No
cyclic_pitch_control_scalar_negative

This parameter scales the pitch cyclic controls.

Default value is 1.

Float No
pedal_control_scalar

This parameter scales the pedal controls. This is a legacy parameter, and should only be used when use_modern_surfaces is set to 0 (FALSE).

Default value is 1.

Float No
pedal_yaw_control_scalar

This parameter scales the pedal controls. This should only be used when use_modern_surfaces is set to 1 (TRUE).

NOTE: This parameter can be used on legacy aircraft as well, but it will be cummulative with pedal_control_scalar, and so you should only use one or the other.

Default value is 1.

Float No
collective_increment

The size of the increments for the collective when using the COLLECTIVE_INCR and COLLECTIVE_DECR events. Value should be between 0 and 1.

Defaults value is 0.05.

Float No
collective_on_rotor_torque_scalar This parameter scales the collective impact on rotor torque.NOTE: This parameter will only be used when the use_modern_surfaces parameter is set to 0.Default value is 1. Float No
collective_to_throttle_correlator

Defines the ratio - from 0 to 1 - with which the collective lever control position is added to the twist grip throttle control position. This will then be applied to the engine(s). The actual equation looks like this:

throttle = throttle_control + collective_control * collective_to_throttle_correlator

Note that if the parameter is set to 0 or is omitted (and all other collective-to-throttle parameters are also omitted) then the engine throttle will work as a simple throttle twist grip control.

IMPORTANT: If you use this parameter, then you cannot use collective_to_throttle_correlator_1d or collective_to_throttle_correlator_2d.

Float No
collective_to_throttle_correlator_1d

This defines the relationship between the collective control position and the twist grip throttle. In this case the throttle applied to the engine(s) is calculated as the sum of the twist grip throttle control position and the result of linear interpolation from this table, depending on the collective control position:

throttle = throttle_control + f (collective_control)

There can be between 2 to 7 pairs of values in this table, and if the dimensions of the table are outside of these bounds, this parameter will be ignored. Values should be between 0 and 1.

Note that if the parameter has all values set to 0 or it is omitted (and all other collective-to-throttle parameters are also omitted) then the engine throttle will work as a simple throttle twist grip control.

IMPORTANT: If you use this parameter, then you cannot use collective_to_throttle_correlator or collective_to_throttle_correlator_2d.

List of Floats

No
collective_to_throttle_correlator_2d

This is a 2D table where

  • The top row corresponds to the twist grip throttle control position, from 0 to 1
  • The left column corresponds to the collective control position, from 0 to 1
  • All other values correspond to the ratio between these two controls, also from 0 to 1.

Together they define the throttle control for all helicopter engines using a 2D linear interpolation of the given values. This can be used to help maintain nominal rotor RPM when the pilot moves the collective lever. For example:

throttle_correlator_table =
0.0    :0.0    :0.5     :1,
0.0    :0.0    :0.18    :0.36,
0.25   :0.0    :0.26    :0.52,
0.5    :0.0    :0.34    :0.68,
0.75   :0.0    :0.42    :0.84,
1      :0.0    :0.5     :1 ;

This parameter has no default values, but if it is omitted from the CFG file (and all other collective-to-throttle parameters are also omitted), or the size of the table exceeds the maximum permitted size (see the note below) then the engine throttle will work as a simple throttle twist grip control.

NOTE:
- You can have from 3 to N rows (including the top row with the twist grip throttle values)
- You can have from 2 to N columns (including the left column with the collective values).
- The combined number of entries (rows * columns) cannot exceed 49. So you could have, for example, 3 rows and 16 columns (48 entries) but not 5 rows and 10 columns (50 entries).

2D Table of Floats

No
collective_move_rate_limit

This sets the limit on the maximum speed of movement by the collective. The value given here is a ratio that must be 0 or greater, where the limit is calculated as ratio / sec. If set to 0, then there is no limit imposed.

Default value is 1.

Float No
cyclic_move_rate_limit Sets the maximum speed of cyclic movement. The value given here is a ratio that must be 0 or greater, where the limit is calculated as ratio / sec. If set to 0, then there is no limit imposed.

Default value is 1.

Float No
rudder_pedals_move_rate_limit Sets the maximum speed of movement for the rudder pedals. The value given here is a ratio that must be 0 or greater, where the limit is calculated as ratio / sec. If set to 0, then there is no limit imposed.

Default value is 1.

Float No
stabilizer_cyclic_scale

If a stabilizer is present and enabled, this is the ratio of assistance it will provide the cyclic.

Default value is 0.

Float No
stabilizer_rudder_scale

If a stabilizer is present and enabled, this is the ratio of assistance it will provide the rudder.

Default value is 0.

Float No
engine_internal_moi

This is the internal moment of inertia of the moving parts of one engine for the clutch simulation and the unclutched simulation, in lbs per ft2.

Default value is 0.25.

Float No
clutch_maximum_torque_up

This is the clutch simulation maximum clutch torque when the engine RPM is pulled up, in lbf * ft.

Default value is 1000.

Float No
clutch_maximum_torque_down

This is the clutch simulation maximum clutch torque when the engine RPM is pulled down, in lbf * ft.

Default value is 1000.

Float No
clutch_unclutch_time

The time - in seconds - it takes for the clutch to go from 0% to 100% or from 100% to 0%.

Default value is 20.

Float No
engine_trim_min

Sets the minimum ratio of the engine rated RPM that can be set by the trimmer. Value is between 0 and 1. Note that this value will be used by the DECREASE_HELO_GOV_BEEP and INCREASE_HELO_GOV_BEEP key events.

As an example: if your rated rotor RPM is 1000RPM, setting the min to 0.9 and the max to 1.1 will allow you to set the trimmer to a value between 900RPM and 1100RPM.

Default value is 1.

Float No
engine_trim_max

Sets the maximum ratio of the engine rated RPM that can be set by the trimmer. Value must be 1 or greater (up to "inifnity"). Note that this value will be used by the DECREASE_HELO_GOV_BEEP and INCREASE_HELO_GOV_BEEP key events.

As an example: if your rated rotor RPM is 1000RPM, setting the min to 0.9 and the max to 1.1 will allow you to set the trimmer to a value between 900RPM and 1100RPM.

Default value is 1.

Float No
engine_trim_rate

Sets the speed of change of the ratio of the engine rated RPM, calculated as RPM Ratio / sec. Note that this value will be used by the DECREASE_HELO_GOV_BEEP and INCREASE_HELO_GOV_BEEP key events.

Default value is 0.

Float No
assistance_cyclic_pitch_stability_centre

This is used to center the assistance neutral input for the pitch cyclic, in degrees.

NOTE: See the Note On Flight Assistance for additional information.

Default value is -1.15.

Float No
assistance_cyclic_bank_stability_centre

This is used to center the assistance neutral input for the bank cyclic, in degrees.

NOTE: See the Note On Flight Assistance for additional information.

Default value is -5.7.

Float No
assistance_pedal_yaw_stability_centre

This ratio is used to center the assistance neutral input for the pedal.

NOTE: See the Note On Flight Assistance for additional information.Default value is 0.15.

Float No
assistance_pedal_yaw_rotation

This is the ratio of the yaw rotation velocity countering the proportional force.

NOTE: See the Note On Flight Assistance for additional information.Default value is 10.

Float No
assistance_pedal_yaw_maxinput

This is the maximum input ratio for all assistance rudder input.

NOTE: See the Note On Flight Assistance for additional information.Default value is 0.5.

Float No
assistance_pedal_yaw_integralmax

This is the maximum input ratio for the integral part of the assistance rudder input.

NOTE: See the Note On Flight Assistance for additional information.Default value is 0.2.

Float No
assistance_pedal_yaw_integralspeed

This is the ratio of the yaw rotational velocity countering the integral force.

NOTE: See the Note On Flight Assistance for additional information.Default value is 1.

Float No
assistance_cyclic_drotation

This is the ratio of the pitch and bank rotational velocity countering the proportional force.

NOTE: See the Note On Flight Assistance for additional information.Default value is 0.

Float No
assistance_cyclic_pitch_rotation

This is the ratio of the pitch and pitch angle countering the proportional force.

NOTE: See the Note On Flight Assistance for additional information.Default value is 2.

Float No
assistance_cyclic_bank_rotation

This is the ratio of the pitch and bank angle countering the proportional force.

NOTE: See the Note On Flight Assistance for additional information.Default value is 2.

Float No
assistance_cyclic_forwardspeed

This is the ratio of the forward speed countering the proportional force.

NOTE: See the Note On Flight Assistance for additional information.Default value is 0.01.

Float No
assistance_cyclic_sidespeed

This is the ratio of the side speed countering the proportional force.

NOTE: See the Note On Flight Assistance for additional information.Default value is 0.01.

Float No
assistance_cyclic_integralmax

This parameter defines the maximum stabilization bank or pitch angle integral - in degrees - for horizontal motion, countering the bank angle integral.

NOTE: See the Note On Flight Assistance for additional information.Default value is 5.

Float No
assistance_cyclic_integralspeed

This is the ratio of the horizontal speed for horizontal motion countering the bank angle integral.

NOTE: See the Note On Flight Assistance for additional information.Default value is 0.2.

Float No
assistance_cyclic_maxinput

This is the maximum input ratio for all assistance cyclic input.

NOTE: See the Note On Flight Assistance for additional information.Default value is 0.15.

Float No
assistance_cyclic_maxspeed

This is the maximum speed - in ft per second - for the cyclic assistance. At a speed of 0 ft per second, the assistance works at 100%. At the specified maxspeed, or above, the assistance is disabled, and in between it gradually decreases.

NOTE: See the Note On Flight Assistance for additional information.Default value is 100.

Float No
assistance_pedal_maxspeed

This is the maximum speed - in ft per second - for the pedal assistance. At a speed of 0 ft per second, the assistance works at 100%. At the specified maxspeed, or above, the assistance is disabled, and in between it gradually decreases.

NOTE: See the Note On Flight Assistance for additional information.Default value is 133.

Float No
governor_pid

The PID to control the auto throttle governor. The table requires the following 5 inputs:

Proportional factor,
Integral factor,
Derivative factor,
I boundary,
D boundary

Default values are: 0, 0, 0, 0, 0

 

For more information on these PID controller parameters, please see the section on PID Parameters.

List of 5 Floats

(see Data Types for more information).

No

 

Note On Flight Assistance

The different assistance_ parameters are provided to pre-initialise the PID that is used for assistance, and will only be used when flight assistance is enabled. The way the PID works is that it will converge towards a value which makes it possible to stabilize the helicopter in hover, and it's the assistance_xxxx_xxxx_stability_centre that you can use to pre-initialise the PID. This will make it start directly at the value that stabilizes the helicopter, so it doesn't "search" as much before stabilizing and is more quickly stable. Note too that there are limits to stabilisation, and if you are too off-center it sometimes does not stabilise at all.

 

 

[FUSELAGE_AERODYNAMICS]

This section is for setting up the aerodynamics of a helicopter fuselage.

 

The available parameters are:

 

Parameter Description Type Required
use_modern_surfaces

When this is set to 0, it will tell the simulation to use the "legacy" helicopter flight model. However setting this to 1 will select the modern flight model, based on surfaces and CFD calculations.

Default value is 0.

Float No
drag_force_cf

This is the drag coefficient of the front facing fuselage.

Default value is 0.

Float No
side_drag_force_cf

This is the drag coefficient of the side facing fuselage.

Default value is 0.

Float No
pitch_damp_cf

The pitch damping coefficient.

NOTE: This parameter will only be used when the use_modern_surfaces parameter is set to 0.Default value is 1.

Float No
pitch_stability_cf

The pitch stability coefficient.

NOTE: This parameter will only be used when the use_modern_surfaces parameter is set to 0.Default value is 1.

Float No
roll_damp_cf

The roll damping coefficient.

NOTE: This parameter will only be used when the use_modern_surfaces parameter is set to 0.Default value is 1.

Float No
yaw_damp_cf

The yaw damping coefficient.

NOTE: This parameter will only be used when the use_modern_surfaces parameter is set to 0.Default value is 1.

Float No
yaw_stability_cf

The yaw stability coefficient.

NOTE: This parameter will only be used when the use_modern_surfaces parameter is set to 0.Default value is 1.

Float No
hstab_pos_lon

This sets the relative longitudinal position of the horizontal stabiliser, in ft, relative to the Datum Reference Point.

Default value is -20.

Float No
hstab_pos_vert

This sets the relative vertical position of the horizontal stabilizer, in ft, relative to the Datum Reference Point.

Default value is 0.

Float No
hstab_span

This sets the span of the horizontal stabiliser, in ft.

Default value is 5.

Float No
hstab_area

The area of the horizontal stabiliser, in sqft.

Default value is 0.

Float No
hstab_incidence

The angle of incidence of the horizontal stabiliser, in degrees.

Default value is 0.

Float No
hstab_lift_coef

This is the coefficient of the slope of lift over the AoA for the horizontal stabiliser.

Default value is 3.

Float No
vstab_pos_lon

This sets the longitudinal position of the vertical stabiliser, in ft, relative to the Datum Reference Point.

Default value is -20.

Float No
vstab_pos_vert

This sets the relative vertical position of the vertical stabiliser, in ft, relative to the Datum Reference Point.

Default value is 0.

Float No
vstab_span

This sets the span of the vertical stabaliser, in ft.

Default value is 5.

Float No
vstab_area

The area of the vertical stabiliser, in sqft.

Default value is 0.

Float No
vstab_incidence

The angle of incidence of the vertical stabiliser, in degrees.

Default value is 0.

Float No
vstab_lift_coef

This is the coefficient of the slope of lift over the AoA for the vertical stabiliser.

Default value is 3.

Float No
fuselage_rear_diam_scale

This is the scale of the rear end of the fuselage in relation to the main section.

Default value is 0.25.

Float No
fuselage_rear_pos_vert

The vertical position of the rear end of the fuselage in relation to the main section.

Default value is 3.

Float No
fuselage_position

The position of the fuselage centre - in ft - relative to the Datum Reference Point. The table requires the following 3 inputs:

z, x, y

Default values are: 0, 0, 0.

List of 3 Floats

(see Data Types for more information).

No

 

 

[MAINROTOR]

This section is for setting up the main rotor of a helicopter.

 

The available parameters are:

 

Parameter Description Type Required
TailRotor

Sets whether the rotor is a main rotor or a tail rotor. When set to 0, it's a horizontal lifting rotor, and when set to 1 this defines a secondary vertical stabilization rotor.

Default value is 0.

Float No
Position

The position of the rotor center - in ft - relative to the Datum Reference Point. The table requires the following 3 inputs:

z, x, y

Default values are: 0, 0, 0.

List of 3 Floats

(see Data Types for more information).

No
max_disc_angle

This parameter will work in two different ways depending on the use_modern_surfaces setting:

  • 0 (legacy): this is the maximum angle of the disk when cyclic inputs are at 100%
  • 1 (modern): This is the blade beta when cyclic inputs are at 100%

Default value is 5.

Float No
Radius

The radius of the rotor, in ft.

Default value is 0.

Float No
RatedRpm

The rated rotation speed of the rotor, in RPM.

Default value is 0.

Float No
number_of_blades

The number of blades of the rotor.

Default value is 2.

Float No
weight_per_blade

This is the weight of a single blade of the rotor, in lbs.

Default value is 10.

Float No
weight_to_moi_factor

This defines the weight to MOI ratio for a single blade depending on the mass distribution of the blade.

Default value is 0.577.

Float No
inflow_vel_reference

This defines the reference speed of airflow through the rotor, in ft per second.

NOTE: This parameter will only be used when the use_modern_surfaces parameter is set to 0.

Default value is 20.

Float No
BrakeCircuit

The name - or index - of the electrical Circuit (of the type CIRCUIT_ROTOR_BRAKE) associated with the rotor brake. Use -1 if not electrical, or if this is a tail rotor (since rotor brakes are ignored on tail rotors).

Default is -1.

String

(or Integer)

No
blade_ang_offset

This parameter permits you to align the simulated rotor to the model's visual mesh rotor.

Default value is 0.

Float No
blade_aspect_ratio

This is the aspect ratio of the rotor blade length over width. This is used to determine the width of the rotor within the simulation.

Default value is 20.

Float No
blade_AOA0_lift_slope

This is the slope of the lift coefficient over the AoA for each blade.

Default value is 6.

Float No
blade_AOAStall_lift_slope

This is the slope of the lift coefficient over the AoA for each blade when the blade is stalled.

Default value is 1.

Float No
blade_tip_to_root_lineartwist

This parameter sets the blade twist between tip and root, in degrees.

Default value is 7.

Float No
blade_AOAStall_scaler

This value inversely scales the AoA angle at which the blade will stall, in degrees.

Default value is 1.69.

Float No
blade_AOAStall_power

This value inversely exponentiates the AoA angle at which the blade will stall.

Default value is 2.

Float No
blade_AOA0_inddrag_efficiency

This value defines the lift induced drag coefficient.

Default value is 0.1.

Float No
blade_AOA0_parasiticdrag

This value defines the blade parasitic drag coefficient.

Default value is 0.005.

Float No
blade_thickness_ratio

This defines the rotor blade width over thickness aspect ratio, and permits the simulation to determine the blade thickness.

Default value is 0.05.

Float No
blade_beta_input_max

This value sets the rotor beta at maximum collective input.

Default value is 10.

Float No
blade_beta_input_min

This value sets the rotor beta at minimum collective input.

Default value is 0.

Float No
blade_flap_rigidity

This value defines the blade rigidity coefficient for flapping dynamics, and will be used to generate phase lag.

Default value is 50.

Float No
blade_flap_inertia

This value defines the blade inertia coefficient for flapping dynamics, and will be used to generate phase lag.

Default value is 0.1.

Float No
blade_lowAOADragAddAng

This value defines the angle of AoA below which there will be an increase of drag.

Default value is -100.

Float No
blade_lowAOADragAddForce

This value defines the intensity of the increase of drag at low AoA angles.

Default value is 0.

Float No
blade_hiAOADragAddAng

This value defines the angle of AoA above which there will be an increase of drag.

Default value is 100.

Float No
blade_hiAOADragAddForce

This value defines the intensity of the increase of drag at high AoA angles.

Default value is 0.

Float No
blade_tip_liftscale

This value defines the ratio of the remaining lift at blade tips because of lift lost for induced drag.

Default value is 1.

Float No
coning_ratio_load_factor_one

This value sets the rotor coning ratio when the load factor is one (a load factor of one represents conditions in straight and level flight, where the lift is equal to the weight).

Default value is 0.1.

Float No
coning_ratio_load_factor_two

This value sets the rotor coning ratio when the load factor is two (a load factor of two approximates the load factor during a maneuver like a turn with a 60º bank angle).

Default value is 0.25.

Float No
coning_angle_at_ratio_one

This value defines the rotor coning angle when the coning factor is 1 (in degrees).

Default value is 6.

Float No
input_to_disk_angle_scale

scale of the input on the disc angle to allow for dead zones and trim countering

Default value is 1.

Float No
gyro_precession_scalar

This value permits you to scale the gyroscopic precession of the rotor.

Default value is 1.

Float No
Reverse_rotation

A value of 0 (FALSE) here will maintain the default rotational direction of the helicopter blades, which is clockwise (when viewed from above). Setting this to 1 (TRUE) will reverse that rotation, so anti-clockwise.

Default value is 0.

Bool No
static_pitch_angle

This parameter defines the neutral static pitch angle, in degrees.

Default value is 0.

Float No
static_bank_angle

This parameter defines the neutral static bank angle, in degrees.

Default value is 0.

Float No
cyclic_pitch_centre

This parameter describes the rotor axis default deflection, according to the helicopter design. This affects not only the tendency of the helicopter to pitch or roll when hands are free, but also the angular position of its body under the rotor in the flight. Values should be between -1 and 1.

Default value is 0.

Float No
cyclic_bank_centre

This parameter describes the neutral point the of cyclic control (like a default "trimmer"), which basically only affects the tendency of a helicopter to pitch or roll when hands are free. Values should be between -1 and 1.

Default value is 0.

Float No
cycl_y_on_cycl_y

This parameter allows you to reduce how much the cyclic input adjusts the pitch of the rotor blades.

By reducing cycl_y_on_cycl_y and increasing cycl_y_on_collective, one can get a duel rotor helicopter (like the Chinook) to pitch forward and backward using a difference in lift between the front and rear rotor.

NOTE: This parameter is only used when your helicopter has the TailRotor parameter set to 0 (FALSE).

Default value is 1.

Float No
cycl_y_on_collective

This parameter allows you to increase how much the cyclic input will adjust the collective setting of the rotor blades.

By reducing cycl_y_on_cycl_y and increasing cycl_y_on_collective, one can get a duel rotor helicopter (like the Chinook) to pitch forward and backward using a difference in lift between the front and rear rotor.

NOTE: This parameter is only used when your helicopter has the TailRotor parameter set to 0 (FALSE).

Default value is 0.

Float No
pedal_on_bank

When set to a value greater than 0, this parameter will allow the pilot to control the bank of the rotor, with the pedals in order to make the helicopter yaw.

NOTE: This parameter is only used when your helicopter has the TailRotor parameter set to 0 (FALSE).

Default value is 0.

Float No
pedal_on_cycl_x

When set to a value greater than 0, this parameter will allow the pilot to control the pitch of the rotor, with the pedals in order to make the helicopter yaw (For helicopters that have 2 main rotors that are one over the other>, creating more drag on one rotor while reducing drag on the rotor spinning in the opposite direction, will yaw the helicopter).

NOTE: This parameter is only used when your helicopter has the TailRotor parameter set to 0 (FALSE).

Default value is 0.

Float No
pedal_on_collective

When set to a value greater than 0, this parameter will allow the pilot to yaw the helicopter using rotor drag.

NOTE: This parameter is only used when your helicopter has the TailRotor parameter set to 0 (FALSE).

Default value is 0.

Float No

 

 

[SECONDARYROTOR]

This section is for setting up the secondary rotor of a helicopter. The parameters in this section are the exact same as those listed for the [MAINROTOR] section, above.

 

 

[BALLOON]

This section is used to setup some parameters that are only relevant when the aircraft you are creating is a hot air ballon of some kind.

 

The available parameters are:

Parameter Description Type Required
balloon_volume This value defines the volume of the balloon's envelope, in ft³. Float Yes
(if aircraft Category is "HotAirBalloon")
balloon_area This value defines the volume of the balloon's envelope, in ft². Float Yes
(if aircraft Category is "HotAirBalloon")