Page ContentsPage Contents (click to expand)
  1. [VERSION]
  2. [GENERALENGINEDATA]
  3. [PISTON_ENGINE]
  4. [PROPELLER]
  5. [TURBINEENGINEDATA]
    1. Note On Corrected Values
  6. [TURBOPROP_ENGINE]
  7. [JET_ENGINE]
  8. [ANTIDETONATION_SYSTEM.N]
  9. [NITROUS_SYSTEM.N]
  10. [DISABLED_CONTROLS]

ENGINE CONFIG DEFINITION

The engines.cfg file is an optional aircraft file for defining engine behaviors and characteristics. Below you can find information on the different sections used in the engines.cfg file as well as what parameters and values are expected within them.

NOTE: to help with the configuration of the Engine configuration (and the Flight Model Config Definition) 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): PlanePerformanceSpreadsheet.xlsx

 

 

[VERSION]

The  [VERSION] section provides version information for the configuration file. In Microsoft Flight Simulator, 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

 

 

[GENERALENGINEDATA]

Every type of aircraft, even a glider, should have this section in the engines.cfg file. Basically, this section describes the type of engine, the number of engines, where the engines are located, and a fuel flow scalar to modify how much fuel the engine requires to produce the calculated power. The parameters available are:

 

Parameter Description Type Required
engine_type Value that identifies what type of engine is on the aircraft.

Integer:

  1. 0 = Piston
  2. 1 = Jet
  3. 2 = None
  4. 3 = Helo-turbine
  5. 4 = Rocket (not supported)
  6. 5 = Turboprop.
Yes
fuel_flow_scalar

This is a scalar value for modifying the fuel flow required by the engine(s) with an impact on the rate at which fuel tanks empty only. Allows you to easily adjust the fuel consumption of the engine without changing any other aspect. A value of less than 1.0 causes a slower fuel consumption for a given power setting, a value greater than 1.0 causes the aircraft to burn more fuel for a given power setting.

Float Yes
min_fuel_press_for_combustion_psf

The minimum fuel pressure required to get a combustion (in psf).

Default is 0.01.

Float No
min_throttle_limit This value defines the minimum throttle position (as a percentage of the maximum). Value is expressed between -1.0 and 1.0, where a negative value is for engines with a reverse mode. Normally this is 0 for piston aircraft and -0.25 for turbine airplane engines with reverse thrust. Float Yes
master_ignition_switch

Defines whether the master ignition switch is available (1, TRUE) or not (0, FALSE). If available, this switch must be on for the ignition circuit, and thus the engines, to be operable. Turning it off will stop all engines.

Default is 0 (FALSE).

Bool No
starter_type

The engine starter type.

Default is 0.

Integer:

0 = Electric
1 = Manual
2 = Bleed Air

No
requires_priming

If set to 1 (TRUE), the engine may need to be primed before combustion (depending on temperature). Set to 0 (FALSE) otherwise.

Default is 1 (FALSE).

Integer No
max_contrail_temperature

The ambient temperature below which engine vapor contrails will be turned on. For piston engines, the contrail effect is turned off unless a temperature value is set here, and for turbine engines the effect will occur automatically.

Default is -39.724 (for turbine engines above 27,362 ft), or set to -1 for no contrails.

Float Yes
accumulated_time_hobbs_min_pct_rpm

This can be used to configure the percentage RPM threshold of detection for measuring how long the engine has been running.

Default is -1 (ie: no threshhold).

Float No
accumulated_time_hobbs_min_knots

This can be used to configure the airspeed threshold of detection for measuring how long the engine has been running.

Default is 25 Knots.

Float No
Engine.N

Offset of the engine  N  thrust position from the Datum Reference Point. Each position takes a list of three values:

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

Each location N specified increases the engine count (maximum of four engines allowed i.e: N is between 0 and 3), and all values are specified in ft. For propellor/turboprop aircraft, this point of thrust is where the propellor is on the engine, and for jet engines, it's the point of thrust output for the engine.

Note that these coordinates are important as they impact the rotation moments generated by engine thrust and will also impact the location of engine wash.

Default is 0, 0, 0.

List of 3 Floats Yes
ThrustAnglesPitchHeading.N

Thrust pitch and heading angles (in degrees) for engine number N, expressed as two values:

  • Value 1 is the pitch (theta x) where:
    • <0° is pitch down
    • >0° is pitch up
  • Value 2 is the heading (theta y) where:
    • <0° is heading left
    • >0° is heading right.

This will affect the direction of thrust for the engine.

Default is 0, 0.

List of 2 Floats No

 

 

[PISTON_ENGINE]

A piston engine's power can be determined through a series of equations that represent the Otto cycle of a four-stroke piston engine, multiplied by the number of pistons available. This section contains all the information needed to be able to determine how much power the engines are capable of producing. Power can also be scaled from the calculated values generated for piston engines with the power_scalar property. If the aircraft being defined has no piston engines this section can be omitted.

 

The parameters available are:

 

Property Description Type Required
cylinder_displacement

Cylinder displacement for each cylinder in cubic inches. This will affect the cylinder torque.

Float Yes
compression_ratio The compression ratio of each cylinder. This will affect the cylinder torque. Float Yes
number_of_cylinders Engine cylinder count. Will affect the total torque sum of all cylinder torques and the total engine friction of all cylinders. Integer Yes
max_rated_rpm The maximum rated RPM of the piston engine. Should be set to the actual aircraft max rated rpm and should not be used to tweak engine performance. Float Yes
max_rated_hp The maximum rated power of the piston engine. Should be set to the actual aircraft max rated power and not be used to tweak engine performance. This value is affected by the power_scalar. Has a direct impact on fuel flow but no direct impact on engine torque or output power. The output power needs to be adjusted to actually meet this value, as it won't be met automatically. Float Yes
power_scalar

Scalar used to ponderate the max_rated_hp value, scaling the net torque / power output of the engine that is transferred to the propeller.

Here is a simplified formula to understand the engine torque output:

Torque = power_scalar * ((CylinderTorque * MechanicalEfficiency) - (CylinderFriction * OilViscosity))

This formula allows to understand how the power_scalar affects the net output.

Default is 1.0.

Float No
two_stroke_cycle

Sets whether the engine is a two stroke cycle engine (TRUE, 1) or not (FALSE, 0).

Default value is 0 (FALSE).

Bool No
carb_icing_sensiblity

How sensitive the carburetor is to icing.

Default value is 0.25.

Float No
starter_time

Time (in seconds) during which the starter will be enabled when toggled on.

Default is 1.5 seconds.

Float No
max_design_mp

This parameter works in two "modes" depending on whether the turbocharged parameter is set to TRUE or not. When set to TRUE, this value indicates the maximum design manifold pressure supplied by the turbocharger, in inHg. When turbocharged is set to FALSE, this sets the value the manifold pressure regulator should not exceed (essentially the maximum value the regulator will authorize), in inHg.

Default value is 0.

Float No
min_design_mp

If a turbocharger is present, this value indicates the minimum design manifold pressure supplied by the turbocharger, in inHg.

Default value is 0.

Float No
normalized_starter_torque

This value can be modified to increase/decrease the torque supplied by the starter to get the prop turning. Increase this value for a greater torque effect, decrease it for a lower torque setting, and the value cannot go below 0, and is usually less than 1.

Default value 0.3.

Float No
auto_ignition

Sets whether auto-ignition is available (TRUE, 1) or not (FALSE, 0). When auto ignition is absent, magnetos need to be enabled for the engine to function. With auto ignition, there is no need to enable magnetos.

Default value is 0 (FALSE).

Bool No
shaft_torque_tc

Gives the speed at which the shaft torque reaches its target value (not applicable for legacy FSX aircraft).

Default value is 2.

  No
carb_heat_delta_temp

Gives the delta of temperature - in Rankine - when the carburetor Heater is activated.

Default value is 27.

Float No
induction_air_temp_tc Give the speed at which the Induction Air Temp increases to reach it's target value. Default value is 0.7. Float No
cooling_type

An integer value indicating the method of engine cooling.

Default value is 0.

Integer:

0 = air cooled
1 = liquid cooled

No
emergency_boost_type

Integer value indicating the emergency boost type available. The emergency boost system was originally designed to model the systems used on WWII aircraft, however it also models water/methanol systems available for more modern aircraft, and is a way to generate a power setting that is actually above the max continuous rating of the engine.

Default value is 0 (none).

Integer:

0 = None
1 = Water Injection
2 = Methanol/Water Injection
3 = WEP

No
max_emergency_boost_time

The emergency boost duration (in seconds) When this time has elapsed, the engine will be considered as "damaged" and have greatly reduced power. Please see the Notes On Emergency Boost for more information.

If not specified, the default values are 315 seconds for WEP and 312 seconds for methanol-water injection.

Float No
emergency_boost_mp_offset

Additional manifold pressure supplied by emergency boost, if available. Value is in inHg.

Default value is 0.

Float No
emergency_boost_mp_damage

Defines the manifold pressure above which - when emergency boost is activated and running - the simulation will start measuring how much time you spent with emergency boost running until you reach the time limit. Value is in inHg. Please see the Notes On Emergency Boost for more information.

Default value is 0.

Float No
emergency_boost_gain_offset

Multiplier on manifold pressure due to emergency boost. Value must be greater than 0.0 to have any effect.

Default value is 0.

Float No
emergency_boost_can_be_stopped

Controls whether or not the Emergency Boost can be shut down after it is engaged.

Default value is 1 (TRUE).

Bool No
emergency_boost_throttle_threshold

Threshold at which the emergency boost will boost the engine. This is semi-automatic and will first require that the user activates war emergency power using the simulation input controls (key/gamepad/controller), and then emergency boost will activate when the throttle goes above the threshold set here. Note that this value is only relevant when the emergency_boost_type parameter is set to 3.

The default value is 0.99.

Float No
turbocharged

Value to indicate if the engine is turbocharged (TRUE, 1) or not (FALSE, 0). Note that you cannot set this to TRUE if the manifold_pressure_regulator parameter is enabled, as they are mutually exclusive systems.

Default is 0 (FALSE).

Bool No
critical_altitude

Altitude, in ft, at which the turbocharger - if present - will provide the maximum design manifold pressure. Above this altitude, the reciprocating engine will no longer produce its rated horsepower even with its throttle wide open.

Default value is 0.

Float No
supercharged

Sets whether the engine is supercharged (1, TRUE) or not (0, FALSE). If the parameter new_supercharged is set to either 1 or 2, then this parameter should be set to FALSE (0), or be omitted from the CFG file. Please see the Notes On Supercharger section for additional information on this feature.

Default value is 0 (FALSE).

Bool

No
new_supercharged

Set the engine to use the modern supercharger formulas using one of the 2 possible models, or set to 0 to use the legacy version. If set to 1 or 2, the supercharged parameter should be set to 0 or omitted from the CFG file. If set to 0, then the supercharged parameter may be used (although this is only recommended for legacy aircraft). Please see the Notes On Supercharger section for additional information on this feature.

Default value is 0 (FALSE).

Enum:

  • 0 = Off. Use for legacy aircraft.
  • 1 = Use a fixed formula to calculate the supercharger boost.
  • 2 = Use for multi speed supercharger support.
No
supercharger_altitude_gear.N

Gives the pressure altitude (in ft) at which the supercharger gear number N will be engaged. There are a maximum of 5 gears, numbered from 1. This parameter is only used when new_supercharged is enabled, and also requires that supercharged = 2.

Default values are -1, -1, -1, -1, -1.

Float No
supercharger_boost_high_end_gear.N

High end boost given by the supercharger when in gear N. There are a maximum of 5 gears, numbered from 1. This parameter is only used when new_supercharged is enabled, and also requires that supercharged = 2.

Default values are 1, 1, 1, 1, 1.

Float No
supercharger_boost_low_end_gear.N

Low end boost given by the supercharger when in gear N. There are a maximum of 5 gears, numbered from 1. This parameter is only used when new_supercharged is enabled, and also requires that supercharged = 2.

Default values are 1, 1, 1, 1, 1.

Float No
supercharger_power_cost

Percent of horsepower required to drive supercharger.

Default value is 0.

Float No
supercharger_boost_low_end

Multiplier on manifold pressure at low RPM. The actual effect will depend on whether new_supercharged is enabled or not, and also requires that supercharged = 1.

Default value is 1.

Float No
supercharger_boost_high_end Multiplier on manifold pressure at high RPM. 

The actual effect will depend on whether new_supercharged is enabled or not, and also requires that supercharged = 1.

Default value is 1.

Float No
manifold_pressure_regulator

Controls whether or not the engine has a manifold pressure regulator (1, TRUE) or not (0, FALSE). This regulator limits the air entering the manifold by opening or closing depending on the pressure need. To replicate this the waste gate is used as a limiting factor on the total boost instead of as a boosting factor like in the turbocharger. That means that the RECIP_ENG_WASTEGATE_POSITION SimVar will fluctuate between 0% and 100%, and can be monitored. The closer it is to 100% the more it limits the boost.

Note that you cannot have a manifold pressure regulator if the turbocharged parameter is set to TRUE, as they are mutually exclusive systems.

Default value is 0 (FALSE).

Bool No
manifold_pressure_regulator_threshold

Manifold pressure (in inHg) at which the Manifold pressure regulator will start having an effect.

Default value is 0 inHg

Float No
manifold_pressure_regulator_tc

Manifold pressure time constant.

Default value is 0.0.

Float No
manifold_efficiency_table

Gives the relation between the Throttle input and the effect on manifold - essentially giving a way to change the engine idle RPM. Each element of the the table - up to a maximum of 47 elements - is a point defined by a throttle position and an efficiency "scalar", so the table should look like this:

throttle_pos:manifold_efficiency,
throttle_pos:manifold_efficiency,
etc...

For example:

manifold_efficiency_table = 0:0.225, 1:0.97

The default values are: 0:0.2, 1:0.97

2D Table of Floats

(see Data Types for more information)

No
detonation_onset

The manifold pressure (in psi) that if reached or exceeded will lead to the engine detonating.

Default value is -1 (disabled).

Float No
min_cruise_rpm

The minimum RPM for cruise speed.

 

Float Yes
max_cruise_rpm The maximum RPM for cruise speed. Float Yes
max_indicated_rpm The maximum RPM to be shown in the UI RPM indicator instrument. This has no influence on the flight model of the aircraft. Float Yes
min_required_rpm

The minimum required RPM to prevent the engine from shutting down when applying ENGINE_POWER_IDLE.

Default value is 700.

Integer No
max_rpm_mechanical_efficiency_scalar

This is a scalar value that can be modified to tune the mechanical efficiency of the engine at maximum RPM. Increase this value to increase the mechanical efficiency, decrease it to decrease the mechanical efficiency. Value must be greater than 0. This is a modifier that will be used along with the engine_mechanical_efficiency_table.

This is one of the mechanical efficiency scalars that will be applied to the torque formula:

Torque = power_scalar * ((CylinderTorque * engine_mechanical_efficiency_table) - (CylinderFriction * OilViscosity))

This scalar table is applied to the 

Default value is 1.0.

Float No
idle_rpm_mechanical_efficiency_scalar

This is a scalar value that can be modified to tune the mechanical efficiency of the engine at idle RPM. Increase this value to increase the mechanical efficiency, decrease it to decrease the mechanical efficiency. Value must be greater than 0. This is a modifier that will be used along with the engine_mechanical_efficiency_table.

This is one of the mechanical efficiency scalars that will be applied to the torque formula:

Torque = power_scalar * ((CylinderTorque * engine_mechanical_efficiency_table) - (CylinderFriction * OilViscosity))

Default value is 1.0.

Float No
low_rpm_shake_scalar

This scalar value is used to add a realistic shaking motion to piston aircraft based on the number and RPM of the engines.

Default value is 1.0.

Float No
max_rpm_friction_scalar

This is a scalar value that can be modified to tune the internal friction of the engine at maximum RPM. Increase this value to increase the friction, decrease it to decrease the friction. Value must be greater than 0.

This is one of the friction scalars that will be applied to the torque formula:

Torque = power_scalar * ((CylinderTorque * engine_mechanical_efficiency_table) - (CylinderFriction * OilViscosity))

Default value is 1.0.

Float No
idle_rpm_friction_scalar

This is a scalar value that can be modified to tune the internal friction of the engine at idle RPM. Increase this value to increase the friction, decrease it to decrease the friction, (can be used to tune the rpm at which the engine idles). Value must be greater than 0.

This is one of the friction scalars that will be applied to the torque formula:

Torque = power_scalar * ((CylinderTorque * engine_mechanical_efficiency_table) - (CylinderFriction * OilViscosity))

Default value is 1.0.

Float No
rpm_to_oil_pressure_table

Gives the relation between the percentage maximum RPM and the percentage maximum oil pressure in a table with up to 47 elements. For example:
rpm_to_oil_pressure_table = 0:0, 0.1:0.3, 0.2:0.9, 0.519:1, 0.74:1 ;

Default values are: 0:0, 0.185:0.3, 0.519:1, 0.740:1

2D Table of Floats

(see Data Types for more information)

No
rpm_to_fuel_pressure_table

Gives the relation between the percentage maximum RPM and the percentage maximum fuel pressure in a table with up to a 47 elements. For example:

rpm_to_fuel_pressure_table = 0:0, 1000:0.3, 2800:1, 4000:1

The forumla for calculating the fuel pressure is as follows:

FuelPress = fuel_press_tuning_constantfuel_press_max * rpm_to_fuel_pressure_table

Default values are: 0.0:0.0, 500.0:0.3, 1400.0:1.0, 2000.0:1.0

2D Table of Floats

(see Data Types for more information)

No
rpm_on_cht_table

Gives the relationship between the RPM (as a percentage of maximum) and the cylinder head temperature (as a percentage of maximum) in a table of up to  elements. For example:

rpm_on_cht_table = 0.26:0.93, 1:1 ;

Default values are: 0.2:0.6, 0.9:1.0.

2D Table of Floats

(see Data Types for more information)

No
engine_mechanical_efficiency_table

This table represents the engine rotation speed (RPM) versus the different mechanical efficiency coefficients for the given speeds.

This is the mechanical efficiency table that will be applied to the torque formula, modified by the values in the tables max_rpm_mechanical_efficiency_scalar and idle_rpm_mechanical_efficiency_scalar. Essentially you can set this table as required and then tune it by using the other two table parameters. These tables are multipliers that will affect every entry in the table but with a different magnitude:

Here is a simplified version of the torque formula to understand how mechanical efficiency works:

Torque = power_scalar * (CylinderTorque * engine_mechanical_efficiency_table) - (CylinderFric * OilViscosity)

This is a 2D table of 6 paired values. Default values are: 0:0.3, 1000:0.3, 2000:0.3, 3000:0.3, 4000:0.3, 6000:0.3

2D Table of Floats

(see Data Types for more information)

No
engine_friction_table

Defines the friction/torque applied to the engine - especially when shutting down - using a 2D table of 7 paired values. Values are ftlbs for torques, and RPM for engine rotation speeds.

This is one of the friction scalars that will be applied to the cylinder friction of the torque formula.

Here is a simplified version of the torque formula to understand how mechanical efficiency works:

Torque = power_scalar * (CylinderTorque * engine_mechanical_efficiency_table) - (CylinderFric * OilViscosity)

Default values are: -1000:0.3, 0:0.3, 1000:0.3, 2000:0.3, 3000:0.3, 4000:0.3, 6000:0.3

2D Table of Floats

(see Data Types for more information)

No
egt_tuning_constant

The EGT tuning coefficient, which is a global scalar of the exhaust gas temperature.

This is the EGT calculation formula:

EGT = egt_tuning_constant * (egt_peak_temperature * egt_factor_from_pct_power + egt_delta_from_mixture_ratio)

Default value is 1.

Float No
egt_peak_temperature

The EGT peak temperature, in Rankine (calculated as °F + 460).

This is the EGT calculation formula:

EGT = egt_tuning_constant * (egt_peak_temperature * egt_factor_from_pct_power + egt_delta_from_mixture_ratio)

Default value is 0.

Rankine No
egt_tc

The EGT time constant, in seconds. This defines at which speed the effective EGT will reach the target EGT based on the current situation.

The time constant formula works like this:

CurrentEGT = (EGT - CurrentEGT) * DeltaTime * EGTtc

Default value is 0.

Float No
egt_factor_from_pct_power

Gives the EGT temperature factor (to egt_peak_temperature) from the % of power (hp/maxhp).

Default values are:

0.000:0.500, 0.500:0.894, 0.640:0.956, 0.750:0.980, 1.000:1.000 

2D Table of Floats

(see Data Types for more information)

No
egt_delta_from_mixture_ratio

Gives the EGT temperature delta (to current EGT value after factor is applied) from the mixture ratio.

Default values are:

0.043:-100.000, 0.050:-89.7000, 0.067:-50.000, 0.070:0.000, 0.075:-4.900, 0.083:-80.000, 0.108:-120.500

2D Table of Floats

(see Data Types for more information)

No
cht_tuning_constant

Cylinder head temperature tuning constant, which is the global scalar of the cylinder head temperature.

This is the CHT calculation formula:

CHT = CHTTuningConst * ((CHTHeatingConst * RPMCHTTable) - (CHTCoolingConst * CHTCooling))

Value must be 0 or greater to be valid.

Default value is 1.0.

Float No
cht_cooling_constant

Cylinder head temperature cooling constant, which is the scalar of the cylinder head temperature cooling.

This is the CHT calculation formula:

CHT = CHTTuningConst * ((CHTHeatingConst * RPMCHTTable) - (CHTCoolingConst * CHTCooling))

Value must be 0 or greater to be valid.

Default value is 0.

Float Yes
cht_heating_constant

Maximum cylinder head temperature in Rankine. This is the CHT calculation formula:

CHT = CHTTuningConst * ((CHTHeatingConst * RPMCHTTable) - (CHTCoolingConst * CHTCooling))

Value must be 0 or greater to be valid.

Default value is 0.

Float Yes
cht_tc

Cylinder head temperature time constant, in seconds.

Default value is 0.

Float No
cht_liquid_max_cooling

Maximum amount of temperature - in Rankine - that the liquid cooling system of the cylinder head temperature can dissipate.

Default value is 250.

Float No
oil_press_tuning_constant

Oil pressure tuning constant, which is an intermediate scalar of oil pressure.

This is the oil pressure formula:

OilPressure = oil_press_tuning_constant * (oil_press_max * oil_temp_factor_from_rpm + oil_temp_to_oil_pressure_table) + prop_lever_pos_to_oil_pressure_delta_table - AnyOilLeakage

Value must be 0 or greater to be valid.

Default value is 1.

Float No
oil_press_max

The maximum permitted oil pressure in psf.

This is the oil pressure formula:

OilPress = oil_press_tuning_constant * (oil_press_max * oil_temp_factor_from_rpm + oil_temp_to_oil_pressure_table) + prop_lever_pos_to_oil_pressure_delta_table - AnyOilLeakage

Default value is 8640.

Float No
oil_press_tc

Oil pressure time constant used to define at which speed the effective oil pressure will reach the target oil pressure based on the current situation. 

The time constant formula works like this:

CurrentOilPress = (OilPress - CurrentOilPress) * DeltaTime * OilPressTC

Default value is 0.8.

Float No
oil_temp_tuning_constant

Oil temperature tuning constant, a global scalar of the oil temperature.

This is the oil temperature calculation formula:

OilTemp = oil_temp_tuning_constant * (oil_temp_heating_constant * OilTempFactorRPM) - (oil_temp_cooling_constant * OilCooling)

Default value is 1.0.

Float No
oil_temp_cooling_constant

Oil temperature cooling constant, a scalar of the oil temperature cooling system.

This is the oil temperature calculation formula:

OilTemp = oil_temp_tuning_constant * (oil_temp_heating_constant * OilTempFactorRPM - oil_temp_cooling_constant * OilCooling)

Default value is 0.21.

Float No
oil_temp_heating_constant

Oil temperature heating constant defining the maximum oil temperature.

This is the oil temperature calculation formula:

OilTemp = oil_temp_tuning_constant * (oil_temp_heating_constant * OilTempFactorRPM - oil_temp_cooling_constant * OilCooling)

Default value is 700.

Rankine No
oil_temp_tc

Oil temperature time constant, in seconds. This is used to define at which speed the effective oil temperature will reach the target oil temperature based on the current situation.

The time constant formula works like this:

CurrentOilTemp = (OilTemp - CurrentOilTemp) * DeltaTime * OilTempConst

Default value is 0.03.

Float No
oil_temp_to_oil_pressure_table

Gives the pressure differential (in psf) of the oil depending on the temperature (in Rankine) of the oil (not applicable to legacy FSX aircraft) in a table of up to 47 elements. For example:
oil_temp_to_oil_pressure_table = 0:0, 500:-1, 700:-600 ;

This is the oil pressure formula:

OilPress = oil_press_tuning_constant * (oil_press_max * oil_temp_factor_from_rpm + oil_temp_to_oil_pressure_table) + prop_lever_pos_to_oil_pressure_delta_table - AnyOilLeakage

Default values are: 0:0, 500:-1, 700, -600

2D Table of Floats

(see Data Types for more information)

No
oil_temp_factor_from_rpm

Gives the oil temperature factor (to oil_temp_heating_constant) from RPM in a table of up to 5 elements.

Default values are: 0:0.8, 500:0.8, 1250:0.9, 2000:1, 3750:1

2D Table of Floats

(see Data Types for more information)

No
oil_coolant_flaps_effect

Maximum temperature - in Rankine - that the oil coolant flaps can dissipate.

Defaults value is 0.

Float No
prop_lever_pos_to_oil_pressure_delta_table

This table defines the delta in psf of the oil pressure depending on the propeller lever position (from 0 - 1) in a table of up to 47 elements.

Default values are: 0:2160, 1:0.

NOTE: This is only applicable to featherable propellers on TURBOPROP engines.

2D Table of Floats

(see Data Types for more information)

No
radiator_cooling_constant

Radiator cooling constant which is used to scale the radiator cooling.

This is the radiator temperature calculation formula:

RadTemp = RadTuningConst * ( RadHeatConst * RadTempTable - RadCoolConst * RadCool)

Default value is 0.

Float No
radiator_heating_constant

Radiator heating constant, defining the maximum radiator temperature.

This is the radiator temperature calculation formula:

RadTemp = RadTuningConst * ( RadHeatConst * RadTempTable - RadCoolConst * RadCool)

Default value is 0.

Float No
radiator_tc

Radiator time constant which defines the speed at which the effective radiator temperature will reach the target radiator temperature based on the current situation.

The time constant formula works like this:

CurrentRadTemp = (RadTemp - CurrentRadTemp) * DeltaTime * RadTempConst

Default value is 0.

Float No
radiator_tuning_constant

Radiator tuning constant, used as a global scalar of the radiator temperature.

This is the radiator temperature calculation formula:

RadTemp = RadTuningConst * ( RadHeatConst * RadTempTable - RadCoolConst * RadCool)

Default value is 1.0.

Float No
radiator_coolant_flaps_effect

Maximum temperature - in Rankine - that the radiator coolant flaps can dissipate.

Defaults value is 0.

Float No
diesel

If set to 1 (TRUE) then the engine is a diesel engine, in which case it will have no mixture and no magneto. If set to 0 (FALSE) then the engine is not a diesel engine.

Default value is 0 (FALSE).

Bool No
fuel_metering_type

An integer value to indicate the fuel metering type, which is the ECU or the ICU deciding how much fuel to inject into the cylinder.

Default value is 1.

Integer:

0 = Fuel Injected
1 = Gravity Carburetor
2 = Aerobatic Carburetor

No
fuel_air_auto_mixture

Sets whether the automixture is available (TRUE, 1) or not (FALSE, 0). If present the mixture will automatically be set for maximum performance. When set to manual, the mixture needs to be manually adjusted to maintain the required performance.

Default value is 0 (FALSE).

Bool No
BestPowerSpecificFuelConsumption

This value sets the specific fuel consumption at the best power mixture ratio per currently produced unit of net output power. Value must be 0 or greater. This value is used in the fuel flow / fuel consumption formula.

Default value is 0.49.

Float Yes
fuel_press_tuning_constant

Fuel pressure tuning constant, which is the global scalar of the fuel pressure.

This is the fuel pressure calculation formula:

FuelPress = fuel_press_tuning_constant * fuel_press_maxrpm_to_fuel_pressure_table

Default value is 1.0.

NOTE: This is for legacy [FUEL] flow only.

Float No
fuel_press_max

Maximum permitted fuel pressure, in psf

This is the fuel pressure calculation formula:

FuelPress = fuel_press_tuning_constant * fuel_press_max * rpm_to_fuel_pressure_table

Default value is 2370.

NOTE: This is for legacy [FUEL] flow only.

Float Yes
fuel_press_tc

Fuel pressure time constant, in seconds.

Default value is 2.0.

NOTE: This is for legacy [FUEL] flow only.

Float No
number_of_magnetos

Number of magnetos in the engine.

Default value is 2.

Integer No
magneto_order_left_right_both

Sets the order of the magneto switch direction. When set to TRUE (1) this will be:

OFF - LEFT - RIGHT - BOTH - START

When set to FALSE (0), this will be:

OFF - RIGHT - LEFT - BOTH - START

Default value is 0 (FALSE).

Integer No
single_magneto_efficiency

Gives the efficiency ratio of the engine if it is designed for 2 magnetos but only 1 is currently active. Value is a Percent Over 100.

Default value is 0.97.

Float No
recip_stop_arc_degrees

Gives the amplitude of the motion made by a reciprocating engine while it is having a spring compression behavior after it stops producing work (not applicable to legacy FSX aircraft).

Default value is 90.

Float No
recip_stop_arc_restitution

Gives the amount of torque in % restituted when reaching its max arc by a reciprocating engine while it is having a spring compression behavior after it stops producing work (not applicable to legacy FSX aircraft).

Default value is 0.8.

Float No
recip_stop_arc_max_pct_rpm

Gives the percentage max RPM at which a reciprocating engine that stopped producing work will start having a spring compression behavior (not applicable to legacy FSX aircraft).

Default value is 0.04.

Float No
recip_stop_arc_friction_factor

Factor on how much friction affects the reciprocating engine while having a spring compression behaviour (not applicable to legacy FSX aircraft).

Default value is 2.

Float No

 

 

[PROPELLER]

This section is for defining the properties of the propellers on a piston aircraft. The parameters available are:

 

Parameter Description Type Required
propeller_type

This sets the propeller type.

Default value is 0.

Integer:

0 = Constant Speed

1 = Fixed Pitch
 

No
propeller_diameter

This sets the diameter of propeller blades from tip to tip, in ft. Will define the propeller disc area and therefore the amount of air mass that will be accelerated by the propeller. Disc area, RPM and pitch will impact the absorbed power and therefore propeller thrust.

If the max_rated_hp value is less than 300 this will default to 6.883 otherwise it will default to 6.1667.

Float No
propeller_blades

This value indicates the number of blades on the propeller. Value can be 2, 3, or 4 only. Propellers with more blades absorb more power and provide more thrust but should be less efficient.

Default value is 2.

Integer No
propeller_moi

MOI of the propeller, axis and all connected moving parts, in Slug sqft. This moment of inertia will define at what speed the engine will reach it's stable RPM. A large MOI results in an engine taking a lot of time going up into RPM.

Default value will be calculated using the following formula: 0.7 * propeller_blades * (propeller_diameter / 2) ^ 3

Float No
use_propeller_rpm

Tells the 3rd person view HUD interface which unit to use for the RPM indication:

  • 0 = engine RPM
  • 1 = propeller RPM

These may not be the same depending on the gear ratio.

Default value is 0.

Integer No
beta_max

Maximum blade pitch angle in degrees for a constant speed prop (this is not used if propeller_type is set to fixed pitch).

Default value is 65.

Float No
beta_cruise

The cruise blade pitch angle in degrees for a constant speed prop (this is not used if propeller_type is set to fixed pitch).

Default value is 30.

Float No
beta_min

Minimum blade pitch angle in degrees for constant speed prop (this is not used if propeller_type is set to fixed pitch).

Default value is 15.

Float No
min_gov_rpm The minimum RPM controlled by the governor for a constant speed prop. For variable pitch propellers, this will be the RPM the system will try to reach when the RPM lever is set to the minimum value. Float Yes
prop_tc

Time constant, in seconds, for the propeller pitch angle changes.

The formula used is:

CurrentPitch = (TargetPitch - CurrentPitch) * prop_tc * DeltaTime

Default value is 0.1.

Float No
prop_governor_p

The propeller governor controller P value. Part of the full PID definition for the propeller.

Default value is 10.

Float No
prop_governor_i

The propeller governor controller I value. Part of the full PID definition for the propeller.

Default value is 1.

Float No
prop_governor_d

The propeller governor controller D value. Part of the full PID definition for the propeller.

Default value is 10.

Float No
prop_governor_iboundary

The propeller governor controller I boundary.

Default value is 100.

Float No
prop_governor_dboundary

The propeller governor controller D boundary.

Default value is 1000.

Float No
prop_cx_min

Value of the propeller Cx when beta = 0.

Default value is 0.06.

Float No
prop_cx_at_cruise_beta

Value of the propeller Cx when beta = beta_max.

Default value is 0.46.

Float No
advance_ratio_on_effective_beta

This is the factor of the advance ratio on the effective beta.

Default value is 0.2.

No longer used by Microsoft Flight Simulator. For legacy aircraft this has been replaced by the table prop_power_cf, or is internally calculated when using the modern flight model.

Float No
prop_cx_parabol

Whether to use the legacy or modern calculation for $C_x$. If set to 0 (FALSE), then the legacy interpolation equations will be used, if set to 1 (TRUE) then the modern parabolic equations will be used.

Default value is 0 (FALSE).

Boolean No
gear_reduction_ratio

The reduction ratio from the engine output RPM to prop RPM.

Default value is 1.

Float No
low_speed_theory_limit

The speed at which low-speed propeller theory gets blended into the high speed propeller theory, measured in ft per second.

This is for legacy FSX, and not used in the modern flight model and should be set to 0 for aircraft that are not legacy. With the legacy FSX propeller model, the simulation did not work at low airspeeds and a fall back simpler simulation was used at lower speeds. This variable allowed you to define the speed below which to change simulation. With the modern flight model, the propeller simulation works at all speeds, including reverse, and there is no need to fallback to the low speed theory.

Default value is 80.

Float No
min_eng_rpm_engage_prop

Value of engine RPM below which the propeller is no longer engaged with the engine and becomes free.

Default value is -1.

Integer No
prop_engage_tc

Speed at which the propeller engages when going above the RPM threshold.

Default value is 0.2.

Float No
prop_disengage_tc

Speed at which the propeller disengages when going below the RPM threshold.

Default value is 0.2.

Float No
fixed_pitch_beta

Propeller pitch, in degrees, that will be used for fixed pitch propellers and all other pitch values will be ignored.

Default value is 20.

Float No
prop_sync_available

This indicates if propeller-sync is available (TRUE, 1) or not (FALSE, 0) for twin engine aircraft. If synchronization between propellers is available then both engines spin at the same RPM.

Default value is 0 (FALSE).

Bool No
prop_deice_available

This indicates if propeller de-icing is available (TRUE, 1) or not (FALSE, 0).

Default value is 1 (TRUE).

Bool No
thrust_scalar

The propeller thrust scalar - a global scalar of propeller thrust applied at the end of the thrust calculation.

Here is the thrust formula:

Thrust = ThrustScalar * ThrustEfficiency * PowerAbsorbed / Airspeed

Default value is 1 and the value must be greater than 0.

Float No
prop_uselegacytables

By default, propeller efficiency and power coefficients are calculated automatically by Microsoft Flight Simulator using the following parameters: prop_scalepowerabs, prop_effminval, prop_effmaxsmooth, prop_falloffpower, prop_falloffcoef, prop_lowbetareductionmid, prop_lowbetareduction.

However you may prefer to tweak these values manually using "legacy" tables. If that is the case, this parameter should be set to 0 (FALSE) or omitted. Setting it to 1 (TRUE) means that the following tables will need to be filled in correctly: prop_efficiency_tableprop_power_cf.

Default value is 0 (FALSE).

Boolean No
prop_scalepowerabs

A scalar value used when calculating the absorbed power by the propeller. Formula uses this value and the number of propeller blades divided by 2.

Only used when prop_uselegacytables is 0 (FALSE) or omitted.

Default value is 1.

  No
prop_effminval

The minimum thrust efficiency of the propeller.

Only used when prop_uselegacytables is 0 (FALSE) or omitted.

Default value is 0.1.

  No
prop_effmaxsmooth

This parameter allows you to add more thrust efficiency at the upper range of the thrust efficiency curve.

Only used when prop_uselegacytables is 0 (FALSE) or omitted.

Default value is 1.

  No
prop_falloffcoef

This is the propeller power curve falloff coefficient.

Only used when prop_uselegacytables is 0 (FALSE) or omitted.

Default value is 0.00045.

Float No
prop_falloffpower

This parameter allows you to define the drop in power of the curve of thrust efficiency at the upper range of the curve.

Only used when prop_uselegacytables is 0 (FALSE) or omitted.

Default value is 8.0.

Float No
prop_lowbetareduction

This parameter allows you to define the thrust effciciency reduction when the beta is far from prop_lowbetareductionmid.

Only used when prop_uselegacytables is 0 (FALSE) or omitted.

Default is 0.03.

Float No
prop_lowbetareductionmid

This parameter allows you to define the beta at which the thrust efficiency will be maximum.

Only used when prop_uselegacytables is 0 (FALSE) or omitted.

Default is 1.4.

Float No
prop_reverse_available

Specifies the scalar on the calculated propeller reverser effect. A value of 0 will cause no reverse thrust to be available. A value of 1.0 will cause the theoretical normal thrust to be available. Other values will scale the normal calculated value accordingly and must be between 0.0 and 1.0.

Default value is 0.

Float No
minimum_on_ground_beta

Minimum blade pitch angle when the aircraft is on the ground, in degrees.

Default value is 0.

Float No
minimum_reverse_beta

Minimum blade pitch angle when the propeller is in reverse, in degrees.

Default value is 0.

Float No
prop_reverse_max_vel

The maximum propeller velocity when reversing. Must be greater than 0 and the default value is 2.

Default value is 2.

Float No
prop_feathering_available

This indicates if propeller feathering is available (TRUE, 1) or not (FALSE, 0). If feathered, the propeller will move to the beta_feather pitch.

Default value is 0 (FALSE).

Bool No
prop_auto_feathering_available

This indicates if propeller auto feathering is available (TRUE, 1) or not (FALSE, 0). If feathered, the propeller will move to the beta_feather pitch.

Default value is 0 (FALSE).

Bool No
min_n1_for_autofeather_armed

Minimum percentage N1 before the AutoFeather system arms itself. 

Default value is 0.

Float No
max_n1_for_autofeather_actuated

The maximum percentage N1 below which the armed AutoFeather system starts to feather the propeller.

Default value is 0.

Float No
min_rpm_for_feather

Minimum RPM at which the prop will feather (if feathering is available).

Default value is 0.

Float No
beta_feather

Propeller pitch angle (in degrees) when feathered.

Default value is 0.

Float No
power_absorbed_cf

Coefficient of friction for power absorbed by a feathered propeller. More power absorbed means more torque and thus more power is required to spin the propeller, but this also means more thrust when the propeller spins. Must be a value between 0.0 and 1.0.

Default value is 0.

Float No
power_propeller_absorbed_cf

This coefficient governs how much power is absorbed by a feathered propeller.

Default value is 1.0. 

Float No
defeathering_accumulators_available

Value to indicate if de-feathering oil accumulators are available (TRUE, 1) or not (FALSE, 0).

Default value is 0 (FALSE).

Bool No
feathering_switches

Boolean indicating if feathering switches are available. 0 = FALSE, 1 = TRUE. Feathering switches (as found on the Douglas DC3), allow the pilot to automatically feather the propeller via a switch, regardless of the propeller lever position.    

Default value is 0 (FALSE).

Bool No
max_pct_torque_for_autofeather_actuated

Maximum % torque before the armed AutoFeather system starts to put the prop in feathering.

Default values is 0.1.

Float No
prop_efficiency_table

The propeller thrust efficiency table formatted as an nD table (13 values per row, up to 7 rows) that defines thrust efficiency based on advance ratio and propeller pitch.

NOTE: This table is only required when the prop_uselegacytables parameter is set to 1 (TRUE), otherwise a formula using parameters is used instead. The advantage of the formula is to provide a continuous smooth result. The advantage of the table is detailed control.

Default values are:

0:0:0.2:0.4:0.6:0.8:1:1.2:1.4:1.6:1.8:2:2.2,
15:0.15:0.4:0.71:0.86:0.72:0.5:0.34:0.23:0.15:0.11:0.08:0.06,
20:0.1:0.3:0.62:0.79:0.86:0.8:0.55:0.42:0.3:0.19:0.12.0.09,
25:0.08:0.23:0.49:0.72:0.82:0.87:0.82:0.6:0.41:0.28:0.18:0.13,
30:0.07:0.18:0.33:0.50:0.72:0.82:0.87:0.85:0.56:0.42:0.26:0.19,
35:0.06:0.16:0.26:0.4:0.55:0.72:0.82:0.86:0.87:0.70:0.4:0.3,
40:0.05:0.12:0.23:0.33:0.45:0.57:0.7:0.81:0.86:0.87:0.85:0.5

nD-table

(see Data Types for more information)

No
prop_power_cf

The propeller power coefficient formatted as an nD table (13 values per row, up to 7 rows) that defines power absorption based on advance ratio and propeller pitch.

NOTE: This table is only required when the prop_uselegacytables parameter is set to 1 (TRUE), otherwise a formula using parameters is used instead. The advantage of the formula is to provide a continuous smooth result. The advantage of the table is detailed control.

Default values are:

0:0:0.2:0.4:0.6:0.8:1:1.2:1.4:1.6:1.8:2:2.2:2.4,
15:0.032:0.029:0.025:0.022:0.009:-0.057:-0.188:-0.338:			-0.522:-0.705:-0.915:-1.092:-1.22,
0:0.062:0.052:0.049:0.042:0.037:0.010:-0.074:-0.188:-0.338:			-0.525:-0.726:-0.942:-1.120,
25:0.098:0.094:0.088:0.08:0.07:0.05:0.02:-0.04:-0.134:-0.272			:-0.468:-0.717:-0.933,
30:0.138:0.132:0.128:0.120:0.110:0.099:0.078:0.04:-0.017:			-0.110:-0.248:-0.468:-0.741,
35:0.206:0.198:0.188:0.178:0.163:0.150:0.130:0.105:0.070:			0.023:-0.074:-0.254:-0.51,
40:0.25:0.242:0.233:0.223:0.214:0.204:0.19:0.175:0.15:0.118:			0.072:0.019:-0.059

nD-table

(see Data Types for more information)

No

 

 

[TURBINEENGINEDATA]

This section is for defining the properties of the turbine engines for an aircraft. If the aircraft being defined has no turbine engines this section can be omitted. Note that most of the parameters here are also used by turboprop aircraft and will require that the [TURBOPROP_ENGINE] section be set up correctly (those parameters that aren't used by TurboProps will be signaled in the descriptions). The available parameters are:

 

Parameter Description Type Required
fuel_flow_gain

The fuel flow gain constant defining at what speed the effective fuel flow will reach the target fuel flow.

No longer used by Microsoft Flight Simulator. Has been replaced by a fuel flow PID which gives more control and precision.

Float No
use_old_fuelflow_simvar

When set to 0 (FALSE) the fuel system will use the modern fuelflow calculations, based on the internal engine simulation corrected fuel flow computations, which means that this internal corrected fuelflow needs to be correctly parametered in order to get the desired consumption.

When set to 1 (TRUE) it will use the old FSX way of doing things, which requires setting the ThrustSpecificFuelConsumption and AfterBurnThrustSpecificFuelConsumption parameters (for Jets) or PowerSpecificFuelConsumption (for TurboProps).

Default value is 0 (FALSE).

Bool No
inlet_area The engine nacelle inlet area, in sqft. This value will scale the ram drag of the turbine in order to use a normalized corrected_airflow_table. Float Yes
rated_N2_rpm The second stage compressor rated RPM at 100%. Float Yes
static_thrust

The max rated static thrust at Sea Level, in lbs at 100% thrust.

NOTE: This parameter is for JET engines only - for turboprop engines, thrust is generated by propellers.

Float Yes
reverser_available

This scalar value is used to set the power available when in reverse. When set to 0, reverser thrust will not be available.

NOTE: This parameter is for JET engines only.Default value is 0. 

Float No
reverser_mach_controlled

Sets if a thrust reverser nozzle is available. When set to 0, the reverser is unavailable. When set to a non 0 value, it enables the thrust reverser and allows you to scale the thrust reverser thrust amount.

NOTE: This parameter is for JET engines only.Default value is 0 (FALSE).

Bool No
afterburner_available

An integer value indicating the number of afterburner stages available. Must be 0 or greater.

NOTE: This parameter is for JET engines only.

Default value is 0 (FALSE).

Integer No
afterburner_throttle_threshold

The throttle range when the afterburner engages, expressed as a Percent Over 100.

NOTE: This parameter is for JET engines only.Default value is 1.

Float No
ThrustSpecificFuelConsumption

The rate of fuel burnt to produce a unit of thrust expressed as a percentage. This is specifically the ratio of fuel used in pounds per hour compared to thrust in pounds (applies at all speeds).

NOTE: This parameter is for JET engines only.

Default value is 0.5.

Float No
AfterBurnThrustSpecificFuelConsumption

The rate of fuel burnt to produce a unit of thrust when afterburners are active. This is specifically the ratio of fuel used in pounds per hour compared to thrust in pounds (applies only when the afterburner is active and will be used instead of the default ThrustSpecificFuelConsumption parameter).

NOTE: This parameter is for JET engines only.Default value is 1.42.

Float No
afterburner_on_thrust_table

This table takes the mach value and a thrust multiplier and outputs a scalar on thrust for maximum afterburner, scaled by the percentage of afterburner active. The table has a maximum of 2x10 values with the following format:

mach:net_thrust_multiplier,	mach:net_thrust_multiplier,
etc...

Default values are:

0.0:1.58, 0.4:1.69, 0.8:1.80, 1.2:1.84, 1.6:1.85, 2.0:1.85

This table is only used when afterburner_available is set to a value greater than 0.

NOTE: This parameter is for JET engines only.

2D Table

(see Data Types for more information)

No
use_n2_to_n1_table

Defines whether or not to use the n2_to_n1_table. When set to 1 (TRUE) this table will be used. When set to 0 (FALSE), the N1 will be calculated based on a formula using high_n1, low_idle_n1, high_n2low_idle_n2 and mach_influence_on_n1.

NOTE: This parameter is for JET engines only.

Default is 1 (TRUE).

Bool No
n2_to_n1_table

This table is used to convert n1 values into to n2 values based on the Mach value. The table has a maximum of 11x13 values with the following format:

0:mach:mach:mach:etc...,
n2:n1:n1:n1:etc...,
n2:n1:n1:n1:etc...,
n2:n1:n1:n1:etc...,
etc...

For example:

n2_to_n1_table=
0.000000:0.000000:0.900000,
0.000000:0.000000:0.000000,
10.000000:2.000000:9.200000,
20.000000:7.000000:14.600000,
30.000000:10.200000:20.000000,
40.000000:15.100000:24.700001,
50.000000:20.100000:32.000000,
60.000000:28.000000:41.799999,
70.000000:38.000000:53.200001,
80.000000:52.000000:67.500000,
90.000000:70.000000:80.800003,
100.000000:89.400002:100.800003,
110.000000:112.000000:120.000000

NOTE: This parameter is for JET engines only.

nD Table

(see Data Types for more information)

No
use_commanded_Ne_table

Defines whether or not use the mach_0_corrected_commanded_ne_table and mach_hi_corrected_commanded_ne_table. When set to 1 (TRUE) these tables will be used. When set to 0 (FALSE), the commanded Ne will be a linear interpolation between idle N1 and 100% N1 based on the throttle input, and the commanded N2 will be equal to the commanded Ne and an N2 to N1 conversion will occur. However, when these tables are used, the commanded N1 will be equal to the commanded Ne.

NOTE: This parameter is for JET engines only.Default is 1 (TRUE).

Bool No
mach_0_corrected_commanded_ne_table

The commanded N2 (corrected) vs. throttle table when at 0 Mach. This table of values (maximum 10x9) uses the delta pressure ratio and the throttle position to calculate a minimum mach which is then used to generate the corrected N2 value. The data in this table is formatted as follows:

lo_mach:PressureRatio0ft:PressureRatio70ft,
%throttle:PressureRatio0ft:PressureRatio70ft,
%throttle:PressureRatio0ft:PressureRatio70ft,
etc...

Note that we use the inverse of delta pressure ratio (Psl/P) so that values are in increasing order, and we give values at 0ft and at 70ft. For example:

mach_0_corrected_commanded_ne_table =
0.000000:1.000000:12.000000,
0.000000:22.000000:27.000000,
0.020000:70.000000:75.000000,
0.166667:74.800003:79.830002,
0.333333:79.699997:84.669998,
0.500000:84.500000:89.500000,
0.666667:89.300003:94.330002,
0.833333:94.199997:99.169998,
1.000000:99.000000:104.000000

NOTE: This parameter is for JET engines only. Please see the Note On Corrected Values as well for further information.

nD Table

(see Data Types for more information)

Yes
mach_hi_corrected_commanded_ne_table

The commanded N2 (corrected) vs. throttle table when at HI Mach. This table of values (maximum 10x9) uses the delta pressure ratio and the throttle position to calculate a maximum mach which is then used to generate the corrected N2 value. The data in this table is formatted as follows:

hi_mach:PressureRatio0ft:PressureRatio70ft,
%throttle:PressureRatio0ft:PressureRatio70ft,
%throttle:PressureRatio0ft:PressureRatio70ft,
etc...

Note that we use the inverse of delta pressure ratio (Psl/P) so that values are in increasing order, and we give values at 0ft and at 70ft. For example:

mach_hi_corrected_commanded_ne_table =
0.900000:1.000000:12.000000,
0.000000:20.000000:25.000000,
0.020000:68.000000:73.000000,
0.166667:72.833336:77.830002,
0.333333:77.666664:82.669998,
0.500000:82.500000:87.500000,
0.666667:87.333336:92.330002,
0.833333:92.166664:97.169998,
1.000000:97.000000:102.000000

NOTE: This parameter is for JET engines only. Please see the Note On Corrected Values as well for further information.

nD Table

(see Data Types for more information)

Yes
use_corrected_N2_from_FF_table

Define whether or not use the corrected_n2_from_ff_table. When set to 1 (TRUE) this table will be used. When set to 0 (FALSE), the N2 will be calculated based on a formula using high_n2, low_idle_n2, high_fuel_flow and idle_fuel_flow.

NOTE: This parameter is for JET engines only. Please see the Note On Corrected Values as well for further information.Default is 1 (TRUE).

Bool No
corrected_n2_from_ff_table

This table describes the relationship between the corrected fuel flow and N2. In the flight model calculations the input for the interpolation is the corrected_FF / static thrust scalar in order to "scale" the input for the engine power. The table requires a maximum of 10x2 inputs and they should have the following format:

corrected_n2:corrected_FF,		corrected_n2:corrected_FF,
etc...

Note that this table depends on the use_corrected_N2_from_FF_table parameter, and if that parameter is omitted or set to 1 (TRUE) then this table is required and has no default values.

NOTE: This parameter is for JET engines only. Please see the Note On Corrected Values as well for further information.

2D Table of Floats

(see Data Types for more information)

No
n1_and_mach_on_thrust_table

This table uses the corrected N1 and Mach as input and outputs a multiplier that will be applied - using bilinear interpolation - to the gross thrust. The table can be a maximum of 11x21, and should have the following format:

0.0:mach:mach:mach:etc...,
n1:multiplier:multiplier:multiplier:etc...,
n1:multiplier:multiplier:multiplier:etc...,
n1:multiplier:multiplier:multiplier:etc...,
etc...

NOTE: Please see the Note On Corrected Values for further information.

nD Table of Floats

(see Data Types for more information)

Yes
corrected_airflow_table This table is used along with the inlet_area value in the computation of Ram Drag for the jet turbine. Input is the corrected N1 and Mach, and output will be the airflow (this is a momentum expressed in Slug sqft). The table can be a maximum of 11x21 and should have the following format:
0.0:mach:mach:mach:mach:etc...,
n1:airflow:airflow:airflow:airflow:etc...,
n1:airflow:airflow:airflow:airflow:etc...,
n1:airflow:airflow:airflow:airflow:etc...,
etc...

NOTE: This parameter is for JET engines only. Please see the Note On Corrected Values as well for further information.

nD Table of Floats

(see Data Types for more information)

Yes
epr_max

The maximum EPR for the engine, as a percentage. The engine EPR is calculated with this formula:

EPR = epr_max * n2_and_mach_to_epr_table * DeltaPressRatio

NOTE: This parameter is for JET engines only.

Default value is 0.

Float Yes
epr_tc

The EPR time constant, in seconds, used to define at which speed the effective EPR will reach the target epr based on the current situation.

The time constant formula works like this:

CurrentEPR = (EPR - CurrentEPR) * DeltaTime * EPRTimeConst

NOTE: This parameter is for JET engines only.

Default value is 0.

Float Yes
epr_tuning_constant

The EPR tuning constant.

Default value is 1.0.

Not currently implimented in Microsoft Flight Simulator. 

Float No
oil_temp_tuning_constant

Oil temperature tuning constant, which is a global scalar of the oil temperature.

This is the oil temperature calculation formula:

OilTemp = oil_temp_tuning_constant * (oil_temp_heating_constant * N1OilTempTable)

NOTE: The N1OilTempTable is not exposed and defined directly in the code.

Default value is 1.0.

Float No
oil_temp_cooling_constant

Oil temperature cooling constant.

Default value is 0.21.

Not currently implemented in Microsoft Flight Simulator. 

Float No
oil_temp_heating_constant

Maximum oil temperature, in Rankine.

This is the oil temperature calculation formula:

OilTemp = oil_temp_tuning_constant * (oil_temp_heating_constant * N1OilTempTable)

NOTE: The N1OilTempTable is not exposed and defined directly in the code.

Default value is 700.

Float No
oil_temp_tc

Oil temperature time constant, in seconds, which defines at which speed the effective oil temperature will reach the target oil temperature based on the current situation.

The time constant formula works like this:

CurrentOilTemp = (OilTemp - CurrentOilTemp) * DeltaTime * oil_temp_tc

Default value is 0.3.

Float No
oil_press_tuning_constant

Oil pressure tuning constant which is an intermediate scalar of oil pressure.

This is the oil pressure formula:

OilPress = oil_press_tuning_constant * oil_press_max * N1_to_oil_pressure_table + prop_lever_pos_to_oil_pressure_delta_table - OilLeakage

prop_lever_pos_to_oil_pressure_delta_table is used with turboprop engines only.

Default value is 1.

Float No
oil_press_max

The maximum permitted oil pressure in psf.

This is the oil pressure formula:

OilPress = oil_press_tuning_constant * oil_press_max * N1_to_oil_pressure_table + prop_lever_pos_to_oil_pressure_delta_table - OilLeakage

prop_lever_pos_to_oil_pressure_delta_table is used with turboprop engines only.

Default value is 8640.

Float No
oil_press_tc

Oil pressure time constant, in seconds, which defines the speed at which the effective oil pressure will reach the target oil pressure based on the current situation.

The time constant formula works like this:

CurrentOilPress = (OilPress - CurrentOilPress) * DeltaTime * oil_press_tc

Default value is 0.8.

Float No
itt_peak_temperature

Set the ITT peak temperature value, in Rankine. 

For jet engines the ITT formula is the following:

ITT = itt_tuning_constant * (itt_peak_temperature * (FuelFlow * (fuel_flow_max_itt_factor - fuel_flow_min_itt_factor) + fuel_flow_min_itt_factor) - ITTCooling)

For turboprop engines, the ITT formula is:

ITT = itt_tuning_constant * (itt_peak_temperature * (FuelFlow * (FuelFlowITTMax - FuelFlowITTMin) + FuelFlowITTMin) - ITTCooling)

NOTE: FuelFlowITTMin and FuelFlowITTMax are not exposed and are defined directly in code.Default value is 0.

Float No
itt_tc

Set the ITT time constant, in seconds, used to define the speed at which the effective ITT will reach the target ITT based on the current situation.

The time constant formula works like this:

CurrentEGT = (ITT - CurrentITT) * DeltaTime * itt_tc

Default value is 0.

Float No
itt_tuning_constant

Set the ITT tuning constant which is the Global scalar of the ITT temperature.

For jet engines the ITT formula is the following:

ITT = itt_tuning_constant * (itt_peak_temperature * (FuelFlow * (fuel_flow_max_itt_factor - fuel_flow_min_itt_factor) + fuel_flow_min_itt_factor) - ITTCooling)

For turboprop engines, the ITT formula is:

ITT = itt_tuning_constant * (itt_peak_temperature * (FuelFlow * (FuelFlowITTMax - FuelFlowITTMin) + FuelFlowITTMin) - ITTCooling)

NOTE: FuelFlowITTMin and FuelFlowITTMax are not exposed and are hard-coded.

Default value is 1.

Float No
fuel_flow_min_itt_factor

Scalar of the ITT temperature at minimum fuel flow.

The ITT formula is the following:

ITT = itt_tuning_constant * (itt_peak_temperature * (FuelFlow * (fuel_flow_max_itt_factor - fuel_flow_min_itt_factor) + fuel_flow_min_itt_factor) - ITTCooling)

NOTE: This parameter is for JET engines only.

Default value is 0.9.

Float No
fuel_flow_max_itt_factor

Scalar of the ITT temperature at maximum fuel flow.

The ITT formula is the following:

ITT = itt_tuning_constant * (itt_peak_temperature * (FuelFlow * (fuel_flow_max_itt_factor - fuel_flow_min_itt_factor) + fuel_flow_min_itt_factor) - ITTCooling)

NOTE: This parameter is for JET engines only.

Default value is 2.

Float No
n1_cooling_factor

Scalar of the ITT temperature cooling.NOTE: This parameter is for JET engines only.

Default value is 0.01.

   
egt_tuning_constant

The EGT tuning constant which is a global scalar of the EGT temperature.

Default value is 1, and value must be 0 or greater.

Float No
egt_peak_temperature

The EGT peak temperature, in Rankine (typically calculated as °F + 460). The EGT temperature is calculated by remapping the ITT temperature to the egt_peak_temperature and correcting it to the temperature ratios.

Default value is 0.

Float No
egt_tc

The EGT time constant, in seconds, used to define the speed at which the effective EGT will reach the target EGT based on the current situation.

The time constant formula works like this:

CurrentEGT = (EGT - CurrentEGT) * DeltaTime * egt_tc

Default value is 0.

Float No
fuel_press_tuning_constant

Fuel pressure tuning constant, which is the global scalar of the fuel pressure.

This is the fuel pressure calculation formula:

FuelPress = fuel_press_tuning_constantfuel_press_maxrpm_to_fuel_pressure_table

Default value is 1.0.

NOTE: This is for legacy [FUEL] flow only.

Float No
fuel_press_max

Maximum permitted fuel pressure, in psf

This is the fuel pressure calculation formula:

FuelPress = fuel_press_tuning_constantfuel_press_maxrpm_to_fuel_pressure_table

Default value is 2376.

NOTE: This is for legacy [FUEL] flow only.

Float No
fuel_press_tc

Fuel pressure time constant, in seconds.

Default value is 2.0.

NOTE: This is for legacy [FUEL] flow only.

Float No
variable_inlet

Sets whether the variable inlet is activated (TRUE, 1) or not (FALSE, 0). If activated, the inlet Mach will be limited to 0.5. If deactivated, the inlet Mach will be limited to 1.0.

Default value is 0 (FALSE).

Bool No
primary_nozzle_available

Sets whether the primary nozzle is activated (TRUE, 1) or not (FALSE, 0).

The primary nozzle formula works like this:

PrimaryNozzle = primary_nozzle_n_mach_to_nozzle_pos + primary_nozzle_afterburner_offset * primary_nozzle_available

Default value is 0 (FALSE).

Bool No
primary_nozzle_afterburner_offset

Sets the primary afterburner nozzle offset, in ft.

The primary nozzle formula works like this:

PrimaryNozzle = primary_nozzle_n_mach_to_nozzle_pos + primary_nozzle_afterburner_offset * primary_nozzle_available

Default value is 0.14.

Float No
primary_nozzle_n1_mach_to_nozzle_pos

This table takes the N1 and Mach as input values, and outputs the nozzle position as a Percent Over 100. The table is a maximum of 4x3 values, and the format is as follows:

0.0:mach:mach,
n1:percent:percent,
n1:percent:percent,
n1:percent:percent

 

The primary nozzle formula works like this:

PrimaryNozzle = primary_nozzle_n1_mach_to_nozzle_pos + primary_nozzle_afterburner_offsetprimary_nozzle_available

Default values are:

0:0:2,
53:0.66:0.1,
65:0.69:0.33,
96:0.7:0.44

nD Table of Floats

(see Data Types for more information)

No
JET_density_on_FF_table

This table allows you to tune the fuel flow to the engine depending on the ambient air density. The table can have up to 10x2 entries, roughly corresponding to the following altitudes:

  1.  - 60k feet
  2.  - 40k feet
  3.  - 35k feet
  4.  - 30k feet
  5.  - 25k feet
  6.  - 20k feet
  7.  - 15k feet
  8.  - 10k feet
  9.  - 5k feet
  10.  - 0k feet

and the parameter format is as follows:

ambient_air_density:fuelflow_multiplier,
ambient_air_density:fuelflow_multiplier,
ambient_air_density:fuelflow_multiplier,
etc...

Default values are:

1.0:0.0,
1.0:0.0

NOTE: This table is for JETS only. For turboprop, use the density_on_ff_table parameter.

2D Table of Floats

(see Data Types for more information)

No
density_on_torque_table

This table allows you to tune the torque that the engine will produce depending on the ambient air density. The table can have up to 10x2 entries, roughly corresponding to the following altitudes:

  1.  - 60k feet
  2.  - 40k feet
  3.  - 35k feet
  4.  - 30k feet
  5.  - 25k feet
  6.  - 20k feet
  7.  - 15k feet
  8.  - 10k feet
  9.  - 5k feet
  10.  - 0k feet

and the parameter format is as follows:

ambient_air_density:torque_multiplier,
ambient_air_density:torque_multiplier,
ambient_air_density:torque_multiplier,
etc...

This is the torque formula for turbo prop engines:

Torque = min(torque_automatic_limit, maximum_torquen1_to_shaft_torque_table * density_on_torque_table *  RPM_on_TP_torque_table)

Default values are:

0.000225:0,
0.000587:0.8,
0.000739:0.83,
0.000891:0.89,
0.001144:0.93,
0.001268:0.970,
0.001496:1,
0.001756:1.025,
0.002049:1.050,
0.002377:1

NOTE: This table is for TURBOPROP only.

2D Table of Floats

(see Data Types for more information)

No
density_on_FF_table

This table allows you to tune the fuel flow to the engine depending on the ambient air density.  This affects the final fuel consumption fuel flow only, not the fuel input and engine performance calculations. Therefore it can be used as a density dependent engine thrust specific fuel consumption scalar.

The table can have up to 10x2 entries, roughly corresponding to the following altitudes:

 - 60k feet
 - 40k feet
 - 35k feet
 - 30k feet
 - 25k feet
 - 20k feet
 - 15k feet
 - 10k feet
 - 5k feet
 - 0k feet

and the parameter format is as follows:

ambient_air_density:fuelflow_multiplier,
ambient_air_density:fuelflow_multiplier,
ambient_air_density:fuelflow_multiplier,
etc...

Default values are:

1.0:0.0,
1.0:0.0

NOTE: This table is for TURBOPROP only. For jets, use the JET_Density_on_FF_table parameter.

2D Table of Floats

(see Data Types for more information)

No
RPM_on_TP_torque_table

This table allows you to tune the shaft torque generated by the engine based on the propeller RPM. The table can have up to 10x2 entries and the parameter format is as follows:

prop_rpm:torque_multiplier,
prop_rpm:torque_multiplier,
prop_rpm:torque_multiplier,
etc...

Default values are:

1.0:0.0,
1.0:0.0

IMPORTANT! This is only relevant for TURBOPROP aircraft.

2D Table of Floats

(see Data Types for more information)

No
starter_N1_max_pct

The percentage of maximum RPM that is reached using only the starter.

Default value is 12.

Float No
starter_N1_rate

The rate at which the starter N1 increases.

Default value is 0.3.

Float No
ignition_auto_type

This value specifies how auto ignition is handled when enabled. This is defined as a comma separated list containing any (or all) of the following:

  • Starter: Active when the starter is
  • Flaps: Active when the flaps are not at 0
  • AntiIce: Active when the engine's anti-ice system is enabled
  • N1: Active when the N1 is below 50%
  • N2: Active when the N2 is below 50%
  • TOGA: Active when the TOGA is active

Default value is Always On (ie: this parameter is an empty string or is omitted).

String (List)

No
min_condition_lever_for_combustion

The minimum position of the condition lever to obtain a combustion, expressed as a  Percent Over 100

Default is 0.01.

Float No
min_n1_for_combustion

The minimum N1 to sustain a combustion without the starter being active.

Default is 10.

Float No
min_n2_for_combustion

The minimum N2 to sustain a combustion without the starter being active.NOTE: This parameter is for JET engines only.

Default is 19.4.

Float No
min_n1_for_starter_cutoff

The minimum N1 at which the starter will be deactivated and the engine should continue to run on its own.

Default is 200 (this is an unreachable value, so that the starter never cuts off automatically).

Float No
min_n2_for_starter_cutoff

The minimum N2 at which the starter will be deactivated and the engine should continue to run on its own.

NOTE: This parameter is for JET engines only.Default is 200 (this is an unreachable value, so that the starter never cuts off automatically).

Float No
n1_normal_tc

The changing N1 acceleration factor during normal use of the engine.

Default value is 1.

Float No
n1_start_max_rate

The limiting N1 acceleration factor during starter use.

Default value is 1.

Float No
n1_start_combustion_max_rate

The limiting N1 acceleration factor during startup when combustion has started.

Default value is 2.

Float No
idle_fuel_flow

The idle fuel flow in lbs per hour.

Default value is 35.

Note that if you are using a turboprop condition lever (see the SimVar TURB_ENG_CONDITION_LEVER_POSITION for more information), then this needs to be set to the same value as idle_high_fuel_flow.

Float No
idle_high_fuel_flow

The idle high fuel flow in lbs per hour.

Default value is 40.

Note that if you are using a turboprop condition lever (see the SimVar TURB_ENG_CONDITION_LEVER_POSITION for more information), then this needs to be set to the same value as idle_fuel_flow.

Float No
low_idle_n1

Set the low idle value for N1, as a percent between 0 and 100, where 100 is the maximum rated N1.

Default value is 50.

Note that if you are using a turboprop condition lever (see the SimVar TURB_ENG_CONDITION_LEVER_POSITION for more information), then this needs to be set correctly.

Float No
low_idle_n2

Set the low idle value for N2, as a percent between 0 and 100, where 100 is the maximum rated N2.

NOTE: This parameter is for JET engines only.

Default value is 50.

Float No
high_n1

Set the high value for N1, as a percent between 0 and 100, where 100 is the maximum rated N1.

Default value is 100.

Float No
high_n2

Set the high value for N2, as a percent between 0 and 100, where 100 is the maximum rated N2.

NOTE: This parameter is for JET engines only.

Default value is 100.

Float No
high_idle_n1

Set the high idle value for N1, as a percent between 0 and 100, where 100 is the maximum rated N1.

Default value is 60.

Note that if you are using a turboprop condition lever (see the SimVar TURB_ENG_CONDITION_LEVER_POSITION for more information), then this needs to be set correctly.

Float No
high_fuel_flow

The high fuel flow in lbs per hour.

Default value is 50.

Float No
min_n2_for_fuel_flow

 

NOTE: This parameter is for JET engines only.

Default value is 15.

Float No
mach_influence_on_n1

 

Default value is 10.

Float No
fuel_flow_max

 

Default value is 10000.

Float No
fuel_flow_controller_p

The turbine flow controller P value. Part of the full PID definition for the propeller.

Default value is 0.01.

Float No
fuel_flow_controller_i

The turbine flow controller I value. Part of the full PID definition for the propeller.

Default value is 0.001.

Float No
fuel_flow_controller_d

The turbine flow controller D value. Part of the full PID definition for the propeller.

Default value is 0.01.

Float No
fuel_flow_controller_iboundary

The turbine flow controller I boundary.

Default value is 10.

Float No
fuel_flow_controller_dboundary

The turbine flow controller D boundary.

Default value is 100. 

Float No
max_torque_protection

The value of the torque triggering a protection by automatically limiting the fuelflow. A value of 0 is no protection.

Default value is 0.

Float No
max_n1_protection

The value at which the N1 triggers a protection by automatically limiting the fuelflow. A value of 0 is no protection.

Default value is 0.

Float No
max_n2_protection

The value at which the N2 triggers a protection by automatically limiting the fuelflow. A value of 0 is no protection.

Default value is 0.

Float No
max_egt_protection

The value at which the EGT triggers a protection by automatically limiting the fuelflow. A value of 0 is no protection.

Default value is 0.

Float No
n2_from_bleed_air_psi_table

Table which contains the N2 generated depending on the pressure of the bleed air from the APU (in psi). For example:

n2_from_bleed_air_psi_table = 0:0, 4:8, 10:18, 18:25 ;

Default values are:

0:0, 4:8, 10:18, 18:25

2D Table of Floats

(see Data Types for more information)

No
bleed_air_on_n2_tc

Time constant which contains the speed at which the bleed air pressure affects the N2 of the turbine, in seconds.

Default value is 1.0.

Float No
N1_to_oil_pressure_table

The percentage N1 to percentage max oil pressure, as a table with a maximum of up to 47 paired elements. For example:

N1_to_oil_pressure_table = 0:0, 0.21:0.88, 0.9:0.954, 1:1

This is the oil pressure formula:

OilPress = oil_press_tuning_constant * oil_press_max * N1_to_oil_pressure_table + prop_lever_pos_to_oil_pressure_delta_table - OilLeakage

prop_lever_pos_to_oil_pressure_delta_table is used with turboprop engines only.

Default values are:

0:0, 0.21:0.88, 0.9:0.954, 1:1

2D Table of Floats

(see Data Types for more information) 

No
min_n2_for_apu_bleed_air_cutoff

Minimum N2 at which the APU bleed air is automatically disabled.

NOTE: This parameter is for JET engines only.

Default is 200 (an unreachable value, so that the starter never cuts off automatically).

Float No
n2_and_mach_to_epr_table

Sets the correspondence between the N2 and Mach to the EPR of the plane. This is defined as a table with a maximum size of 10x9, where:

  • The first entry is a set of mach values (up to 10) - 0:mach:mach:mach
  • Subsequent entries follow the format of n2:EPR:EPR:EPR

For example:

n2_and_mach_to_epr_table = 0.0:0.0:0.45:0.9, 0.0:0.0:0.0:0.0, 56.0:0.76:0.76:1.86, 90.0:1.11:1.11:3.28, 110.0:1.0:1.0:4.23

The engine EPR is calculated with this formula:

EPR = epr_max * n2_and_mach_to_epr_table * DeltaPressRatio

The default values are:

0:0:0.45:0.9,
0:0:0:0,
56:0.751:0.751:1.86,
90:0.957:0.957:3.28,
110.0:1.0:1:4.23

NOTE: This parameter is for JET engines only.

nD Table of Floats

(see Data Types for more information)

No
supersonic_ram_drag

By default, ram-drag calculations are limited to a maximum Mach of 1. Setting this value to 1 will remove this limit, permitting supersonic calculations above mach1 for drag generated by the ingestion of air into the engine. For more information, please see Ram Drag.

Default value is 0.

Integer No
supersonic_inlet

Sets whether the variable inlet is activated (1, TRUE) or not (0, FALSE). For more information please see Turbine Engine Supersonic Inlet.

Default value is 0 (FALSE).

Bool No
supersonic_inlet_efficiency_correction_table

Table to correct the efficiency of the inlet depending on the flight Mach number. Table data should be formatted as 10 paired values, mach:efficiency

Default values are:

1:1, 1:1, 1:1, 1:1, 1:1, 1:1, 1:1, 1:1, 1:1, 1:1

2D Table of Floats

(see Data Types for more information)

No
supersonic_inlet_design_mach

The Mach number at which the airflow will be reduced in the inlet. Acts as a limit on inlet mach.

Default value is 0.5.

Float No
supersonic_inlet_hypersonic

When set to 1 (TRUE), this will allow the inlet to have 50% more efficiency when above Mach 5.0. Useful for hypersonic flight but requires the correct tuning of the n1_and_mach_on_thrust_table and/or supersonic_inlet_efficiency_correction_table to model loss of power.

Default value is 0 (FALSE).

Bool No

 

Note On Corrected Values

The various parameters that use corrected values have their calculations based on the following paper:

  1. GAS TURBINE PARAMETER CORRECTIONS, by Allan J. Volponi
  2. January 2020
  3. DOI: 10.1007/978-3-030-41076-6
  4. ISBN: 978-3-030-41075-9

 

 

[TURBOPROP_ENGINE]

This section defines values for turbo-prop engines and should only be included if the aircraft has this engine type. TurboProp engines will also require that [TURBINEENGINEDATA] section is correctly setup.  Available parameters are:

 

Parameter Description Type Required
power_scalar

Scalar on the turboprop power, which is applied to the maximum_torque value.

Default value is 1.

Float No
maximum_torque

The maximum torque available, in ftlbs at 100% torque Engine torque value if ft-lbs at 100% torque.

This is the torque formula for turbo prop engines:

Torque = min(torque_automatic_limit, maximum_torque * n1_to_shaft_torque_table * density_on_torque_table * RPM_on_TP_torque_table)

Float Yes
torque_automatic_limit

This allows to set the maximum torque limit of the engine for those engines that feature a torque limit.

This is the torque formula for turbo prop engines:

Torque = min(torque_automatic_limit, maximum_torque * n1_to_shaft_torque_table * density_on_torque_table * RPM_on_TP_torque_table)

Default value is 100000000000000.

Float No
engine_friction_table

Defines the friction/torque applied to the engine - especially when shutting down - using a 2D table of up to 8 paired values. Values are ftlbs for torques, and RPM for engine rotation speeds.

Default values are: -1000:0.3, 0:0.3, 1000:0.3, 2000:0.3, 3000:0.3, 4000:0.3, 6000:0.3

No longer used by Microsoft Flight Simulator.

2D Table of Floats

(see Data Types for more information) 

No
tp_idle_range

The increase of N1 idle at high mixture, as a percentage.

Default value is 8.

Note that if you are using a turboprop condition lever (see the SimVar TURB_ENG_CONDITION_LEVER_POSITION for more information), then this needs to be set to 0.

Float No
tp_high_idle_throttle_pos

The throttle position of high idle, as a percentage.

Default value is 0.

Float No
low_idle_n1

The idle N1 with minimal mixture, as a percentage.

Default value is 50.

Float No
n1_to_shaft_torque_table

Sets the correspondence between the corrected N1 and a torque multiplier. This is defined as a table with a maximum of 5 entries, formatted as:

corrected_n1:multiplier,
corrected_n1:multiplier,
corrected_n1:multiplier,
etc...

For example:

n1_to_shaft_torque_table = 0:0, 66:0.05, 100:1, 110:1.1

This is the torque formula for turbo prop engines:

Torque = min(torque_automatic_limit, maximum_torque * n1_to_shaft_torque_table * density_on_torque_table * RPM_on_TP_torque_table)

2D Table of Floats

(see Data Types for more information) 

Yes
rated_shaft_hp

The rated shaft hp for the engine. Note that this is not used for performance calculations, and is only meant only for display purposes.

Default value is 0.

Float No
PowerSpecificFuelConsumption

The fuel consumption based on specific power requirements. Will define the fuel consumption per unit of power of the engine. Scaled by density_on_ff_table.

Turboprops only.

Default value is 0.55.

Float No
free_turbine

Sets whether the engine a free turbine turbo propeller (1 -TRUE) or not (0 - FALSE).

Default value is 0 (FALSE).

Boolean No

 

 

[JET_ENGINE]

This section defines values for jet engines and should only be included if the aircraft has this engine type. Available parameters are:

 

Parameter Description Type Required
thrust_scalar

Tuning scalar coefficient used to ponderate/multiply turbine engine static thrust.

Default value is 1.

Float No

 

 

[ANTIDETONATION_SYSTEM.N]

This section permits you to define the properties of the ADI system for each engine in the aircraft. When defining these parameters, N starts at 0 and goes up to the number of engines - 1. Available parameters are:

 

Parameter Description Type Required
reservoir_size

The size of the ADI reservoir in Gallons.

Default value is 0.

Float No
flow_rate

The rate of flow in Gallons per minute.

Default value is 0.

Float No
reservoir_position

This is a table of floats defining the x,y,z position of the ADI reservoir for the engine, relative to the Datum Reference Point point, in ft.

Default values are:0, 0, 0

ID Table of Floats

(see Data Types for more information) 

No
max_mp_compensate

This sets the manifold pressure above which ADI system cannot compensate. Value is defined in inHg

Default value is 0.  

Float No

 

 

[NITROUS_SYSTEM.N]

Some modern aircraft have a nitrous system that can be used to boost the output of the engines. This section permits you to define some parameters to control this system. When defining these parameters, N starts at 0 and goes up to the number of engines - 1. Available parameters are:

 

Parameter Description Type Required
reservoir_size

The size of the nitrous reservoir in Gallons.

Default value is 0.

Float No
flow_rate

The rate of flow in Gallons per minute.

Default value is 0.

Float No
mp_boost

The multiplier on manifold pressure, in inHg.

Default value is 0.

Float

No

 

 

[DISABLED_CONTROLS]

This section can be used to disable specific controls and can be omitted if not required. Available parameters are:

 

Parameter Description Type Required
DisableFuelValveControls

Disables the fuel valve controls if TRUE (1) otherwise set to FALSE (0).

Default is 0.

Bool No
DisableMixtureControls

Disables the fuel mixture controls if TRUE (1) otherwise set to FALSE (0).

Default is 0.

Note that if you are using a turboprop condition lever (see the SimVar TURB_ENG_CONDITION_LEVER_POSITION for more information), then this needs to be set to 1 (TRUE). 

DisableParkingBrakeControls

Disables the parking brake controls if TRUE (1) otherwise set to FALSE (0).

Default is 0.

DisablePropellerControls

Disables the propeller controls if TRUE (1) otherwise set to FALSE (0).

Default is 0.

DisableAutopilotControls

Disables the autopilot controls if TRUE (1) otherwise set to FALSE (0).

Default is 0.

 

 

 

©2021 Microsoft      Contact Us      Privacy Policy      MSFS Forums      SDK Q&A Support