flight_performance.cfg

The flight_performance.cfg file is an optional aircraft file for checking the performance characteristics of an aircraft for use with tuning the flight model and for correctly configuring flight plans and other applications. Below you can find information on the different sections used in the flight_performance.cfg file as well as what parameters and values are expected within them. However it should be noted that that the information contained in this file has no influence on the aircraft flight behavior, and is instead used to compare computed performance versus expected performance (which can be found in the POH or from industrial or academic data).

IMPORTANT! Currently this file and debug window are only usable by planes with turbine / turbofan engines.

This file is initially created using the Debug Aircraft Flight Performance window, and in this window you can create various configurations. In the generated file, the data for each configuration will be contained in the corresponding numbered section, and there will also be a common section. For example, if you have two configurations, you will have a [AIRCRAFT_CONFIGURATION.0] which is the common section, then you will have [AIRCRAFT_CONFIGURATION.0] (configuration 1) and [AIRCRAFT_CONFIGURATION.1] (configuration 2). This debug window is documented here:

Flight Performance

[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

[AIRCRAFT_GEOMETRY]

This section provides general information about the defined aircraft geometry. The available parameters are:

Parameter	Description	Type	Required
`wing_area`	The total wing area as defined by the `wing_area` parameter in the flight_model.cfg.	Float	Yes
`wing_span`	The wing span as defined by the `wing_span` parameter in the flight_model.cfg.	Float	Yes
`wing_mean_chord`	The mean wing Chord. This value is based on internal calculations. These calculations start by taking the `wing_root_chord`, the number of wings and the `wing_area`, to derive the wing tip chord. This value is then used to get the wing taper ratio, and then, finally, the wing mean chord is calculated using the root and the taper ratio.	Float	Yes

[AIRCRAFT_CONFIGURATION.N]

This section provides general information for the aircraft performance when in flight. The available common (N is 0) parameters are:

Parameter	Description	Type	Required
`configuration_name`	The name of the configuration (as a string). This is purely orientative to help you identify which configuration is being used. NOTE: This parameter is only used when more than one aircraft configuration is present.	String	No
`landing_gear_state`	This defines whether the configuration has been created with landing gear down (1, TRUE) or not (0, FALSE). NOTE: This parameter is only used when more than one aircraft configuration is present.	Boolean	No
`wing_configuration_ID`	This tells the configuration which `[FLAPS.N]` setting to use. NOTE: This parameter is only used when more than one aircraft configuration is present.	Integer	No
`spoilers_angle`	NOTE: This parameter is only used when more than one aircraft configuration is present.
`CL_table_by_AoA`	This is a table that correlates a given AoA (in degrees) with the aircraft lift coefficient (CL). The table is formatted as follows: `CL_table_by_AoA = AoA, AoA, AoA, etc... :: CL, CL, CL, etc...` For example: `CL_table_by_AoA = -5.0, 0.0, 5.0, 10.0, 15.0, 20.0, 25.0 :: -0.22777, 0.29988, 0.75617, 1.08905, 1.28149, 1.34411, 1.40615`	1D Table	Yes
`CD_table_by_Mach_and_AoA`	This is a table that correlates a given speed (in Mach) with a given AoA (in degrees) to give the aircraft drag coefficient (CD). The table is formatted as follows: `CD_table_by_Mach_and_AoA = mach, mach, mach, etc... : AoA, AoA, AoA, etc... :: CD, CD, CD, etc... : CD, CD, CD, etc... : CD, CD, CD, etc... : CD, CD, CD, etc...` For example: `CD_table_by_Mach_and_AoA = 0.000, 0.200, 0.400, 0.600, 0.800 : -5.0, 0.0, 5.0, 10.0, 15.0, 20.0, 25.0 :: 0.02019, 0.01288, 0.01871, 0.03330, 0.04889, 0.05916, 0.08144 : 0.02019, 0.01288, 0.01871, 0.03330, 0.04889, 0.05916, 0.08144 : 0.02019, 0.01288, 0.01871, 0.03330, 0.04889, 0.05916, 0.08144 : 0.02019, 0.01288, 0.01871, 0.03330, 0.04889, 0.05916, 0.08144 : 0.02019, 0.01288, 0.01871, 0.03330, 0.04889, 0.05916, 0.08144`	2D Table	Yes

[ENGINE_PERFORMANCE]

This section contains tables of data related to the aircraft engine performance. Available parameters are:

Parameter	Description	Type	Required
`number_of_engines`	The total number of engines for the aircraft. This is derived from the number of `Engine.N` parameters defined in the engines.cfg.	Float	Yes
`engine_max_revs`	This sets the maximum revolutions for the engines being tested. For Piston Engines, this is the RPM, and for turbine and turbofan engines, this is a percentage. IMPORTANT! Currently only aircraft with turbine / turbofan engines are supported.	Float	Yes
`engine_net_thrust_table_by_OAT_dev_and_altitude_and_Mach_and_throttle`		4D Table	Yes
`engine_fuel_consumption_table_by_OAT_dev_and_altitude_and_Mach_and_throttle`		4D Table	Yes
`engine_corrected_N1_table_by_OAT_dev_and_altitude_and_Mach_and_throttle`		4D Table	Yes
`engine_idle_corrected_N1_table_by_OAT_dev_and_altitude_and_Mach`		3D Table	Yes
`engine_idle_descent_corrected_N1_table_by_OAT_dev_and_altitude_and_Mach`		3D Table	Yes
`engine_max_corrected_N1_table_by_OAT_dev_and_altitude_and_Mach`		3D Table	Yes
`engine_climb_corrected_N1_table_by_OAT_dev_and_altitude_and_Mach`		3D Table	Yes

[TAKEOFF_PERFORMANCE]

This section contains tables of data related to the performance when the aircraft is taking off. Available parameters are:

Parameter	Type	Required
`calculate_distances_based_on_Vspeed_tables`	Boolean	Yes
`takeoff_ground_roll_distance_table_by_weight_and_OAT_and_altitude`	3D Table	Yes
`takeoff_total_distance_table_by_weight_and_OAT_and_altitude`	3D Table	Yes
`V1_table_by_flaps_and_weight`	2D Table	Yes
`Vr_table_by_flaps_and_weight`	2D Table	Yes
`V2_table_by_flaps_and_weight`	2D Table	Yes
`V1_adjustments_table_by_altitude_and_OAT`	2D Table	Yes
`Vr_adjustments_table_by_altitude_and_OAT`	2D Table	Yes
`V2_adjustments_table_by_altitude_and_OAT`	2D Table	Yes
`V1_adjustments_table_by_slope_and_weight`	2D Table	Yes
`V1_adjustments_table_by_wind_and_weight`	2D Table	Yes

[LANDING_PERFORMANCE]

This section contains tables of data related to the aircraft landing performance. Available parameters are:

Parameter Description Type Required

Parameter	Description	Type	Required
`landing_ground_roll_distance_table_by_weight_and_OAT_and_altitude`	This is a table that correlates a given weight (in lbs) with the OAT deviation from ISA (in °C) and a given altitude (in ft) to give the required landing roll distance (in ft). The table is formatted as follows: `landing_ground_roll_distance_table_by_weight_and_OAT_and_altitude = weight, weight, etc... : temperature, temperature, etc... : altitude, altitude, etc... :: dist, dist, etc... : dist, dist, etc... : etc... : etc...` For example: `landing_ground_roll_distance_table_by_weight_and_OAT_and_altitude = 7000, 7500, 8000, 8500 : -10, 0, 10, 20, 30, 40 : 0, 2000, 4000, 6000, 8000, 10000, 12000 :: 755, 810, 875, 940, 1015, 1095, 1185 : 785, 840, 905, 975, 1055, 1140, 1230 : 810, 875, 940, 1015, 1090, 1180, 1275 : 840, 905, 975, 1050, 1130, 1220, 1320 : 870, 935, 1005, 1085, 1170, 1265, 0 : 900, 965, 1040, 1120, 0, 0, 0 : 810, 870, 940, 1010, 1090, 1175, 1270 : 840, 905, 975, 1050, 1130, 1220, 1320 : etc...`	3D Table	Yes
`landing_total_distance_table_by_weight_and_OAT_and_altitude`	This is a table that correlates a given weight (in lbs) with the OAT deviation from ISA (in °C) and a given altitude (in ft) to give the required total landing distance (in ft). The table is formatted as follows: `landing_total_distance_table_by_weight_and_OAT_and_altitude = weight, weight, etc... : temperature, temperature, etc... : altitude, altitude, etc... :: airspeed, airspeed, etc... : airspeed, airspeed, etc... : etc... : etc...` For example: `landing_total_distance_table_by_weight_and_OAT_and_altitude = 7000, 7500, 8000, 8500 : -10, 0, 10, 20, 30, 40 : 0, 2000, 4000, 6000, 8000, 10000, 12000 :: 1485, 1565, 1655, 1750, 1855, 1965, 2090 : 1525, 1610, 1700, 1800, 1905, 2025, 2115 : 1565, 1655, 1745, 1850, 1960, 2080, 2210 : 1605, 1695, 1795, 1900, 2015, 2135, 2270 : 1645, 1740, 1840, 1950, 2065, 2195, 0 : 1690, 1785, 1885, 2000, 0, 0, 0 : 1560, 1645, 1740, 1845, 1955, 2075, 2200 : etc...`	3D Table	Yes

landing_ground_roll_distance_table_by_weight_and_OAT_and_altitude

This is a table that correlates a given weight (in lbs) with the OAT deviation from ISA (in °C) and a given altitude (in ft) to give the required landing roll distance (in ft).

The table is formatted as follows:

landing_ground_roll_distance_table_by_weight_and_OAT_and_altitude = weight, weight, etc... : temperature, temperature, etc... : altitude, altitude, etc... :: dist, dist, etc... : dist, dist, etc... : etc... : etc...

For example:

landing_ground_roll_distance_table_by_weight_and_OAT_and_altitude = 7000, 7500, 8000, 8500 : -10, 0, 10, 20, 30, 40 : 0, 2000, 4000, 6000, 8000, 10000, 12000 :: 755, 810, 875, 940, 1015, 1095, 1185 : 785, 840, 905, 975, 1055, 1140, 1230 : 810, 875, 940, 1015, 1090, 1180, 1275 : 840, 905, 975, 1050, 1130, 1220, 1320 : 870, 935, 1005, 1085, 1170, 1265, 0 : 900, 965, 1040, 1120, 0, 0, 0 : 810, 870, 940, 1010, 1090, 1175, 1270 : 840, 905, 975, 1050, 1130, 1220, 1320 : etc...

3D Table

Yes

landing_total_distance_table_by_weight_and_OAT_and_altitude

This is a table that correlates a given weight (in lbs) with the OAT deviation from ISA (in °C) and a given altitude (in ft) to give the required total landing distance (in ft).

The table is formatted as follows:

landing_total_distance_table_by_weight_and_OAT_and_altitude = weight, weight, etc... : temperature, temperature, etc... : altitude, altitude, etc... :: airspeed, airspeed, etc... : airspeed, airspeed, etc... : etc... : etc...

For example:

landing_total_distance_table_by_weight_and_OAT_and_altitude = 7000, 7500, 8000, 8500 : -10, 0, 10, 20, 30, 40 : 0, 2000, 4000, 6000, 8000, 10000, 12000 :: 1485, 1565, 1655, 1750, 1855, 1965, 2090 : 1525, 1610, 1700, 1800, 1905, 2025, 2115 : 1565, 1655, 1745, 1850, 1960, 2080, 2210 : 1605, 1695, 1795, 1900, 2015, 2135, 2270 : 1645, 1740, 1840, 1950, 2065, 2195, 0 : 1690, 1785, 1885, 2000, 0, 0, 0 : 1560, 1645, 1740, 1845, 1955, 2075, 2200 : etc...

3D Table

Yes

[CLIMB_PERFORMANCE]

This section contains tables of data related to the aircraft climb performance. Available parameters are:

Parameter Description Type Required

Parameter	Description	Type	Required
`climb_IAS_table_by_initial_weight`	This is a table that correlates the initial climb weight (in lbs) with the climb indicated airspeed (in Knots). The table is formatted as follows: `climb_IAS_table_by_initial_weight = weight, weight, etc... :: IAS, IAS, etc...` For example: `climb_IAS_table_by_initial_weight = 3968, 4189, 4407, 4630, 4850, 5071 :: 93, 93, 93, 96, 96, 96`	1D Table	Yes
`average_climb_rate_table_by_initial_weight_and_altitude`	This is a table that correlates a given altitude (in ft) with a given weight (in lbs) to give the average climb rate (in ft / min) from sea level. The table is formatted as follows: `average_climb_rate_table_by_initial_weight_and_altitude = weight, weight, etc... : altitude, altitude, etc... :: climb_rate, climb_rate, etc... : climb_rate, climb_rate, etc...` For example: `average_climb_rate_table_by_initial_weight_and_altitude = 3968, 4189, 4407, 4630 : 0, 2000, 4000, 6000 :: 1440, 1425, 1415, 1405 : 1345, 1335, 1325, 1315 : 1260, 1250, 1240, 1230 : 1175, 1165, 1155, 1140`	2D Table	Yes
`total_fuel_table_by_initial_weight_and_altitude`	This is a table that correlates a given altitude (in ft) with a given weight (in lbs) to give the total amount of fuel consumed (in Gallons) in the climb. The table is formatted as follows: `total_fuel_table_by_initial_weight_and_altitude = weight, weight, etc... : altitude, altitude, etc... :: fuel_gallons, fuel_gallons, etc... : fuel_gallons, fuel_gallons, etc...` For example: `total_fuel_table_by_initial_weight_and_altitude = 3968, 4189, 4407, 4630 : 0, 2000, 4000, 6000 :: 1440, 1425, 1415, 1405 : 1345, 1335, 1325, 1315 : 1260, 1250, 1240, 1230 : 1175, 1165, 1155, 1140`	2D Table	Yes

climb_IAS_table_by_initial_weight

This is a table that correlates the initial climb weight (in lbs) with the climb indicated airspeed (in Knots). The table is formatted as follows:

climb_IAS_table_by_initial_weight = weight, weight, etc... :: IAS, IAS, etc...

For example:

climb_IAS_table_by_initial_weight = 3968, 4189, 4407, 4630, 4850, 5071 :: 93, 93, 93, 96, 96, 96

1D Table

Yes

average_climb_rate_table_by_initial_weight_and_altitude

This is a table that correlates a given altitude (in ft) with a given weight (in lbs) to give the average climb rate (in ft / min) from sea level. The table is formatted as follows:

average_climb_rate_table_by_initial_weight_and_altitude = weight, weight, etc... : altitude, altitude, etc... :: climb_rate, climb_rate, etc... : climb_rate, climb_rate, etc...

For example:

average_climb_rate_table_by_initial_weight_and_altitude = 3968, 4189, 4407, 4630 : 0, 2000, 4000, 6000 :: 1440, 1425, 1415, 1405 : 1345, 1335, 1325, 1315 : 1260, 1250, 1240, 1230 : 1175, 1165, 1155, 1140

2D Table

Yes

total_fuel_table_by_initial_weight_and_altitude

This is a table that correlates a given altitude (in ft) with a given weight (in lbs) to give the total amount of fuel consumed (in Gallons) in the climb.

The table is formatted as follows:

total_fuel_table_by_initial_weight_and_altitude = weight, weight, etc... : altitude, altitude, etc... :: fuel_gallons, fuel_gallons, etc... : fuel_gallons, fuel_gallons, etc...

For example:

total_fuel_table_by_initial_weight_and_altitude = 3968, 4189, 4407, 4630 : 0, 2000, 4000, 6000 :: 1440, 1425, 1415, 1405 : 1345, 1335, 1325, 1315 : 1260, 1250, 1240, 1230 : 1175, 1165, 1155, 1140

2D Table

Yes

[CRUISE_PERFORMANCE]

This section contains tables of data related to the performance when the aircraft is cruising. Available parameters are:

Parameter Description Type Required

Parameter	Description	Type	Required
`cruise_TAS_table_by_weight_and_altitude`	This is a table that correlates a given weight (in lbs) with the OAT deviation from ISA (in °C) and a given altitude (in ft) to give the true airspeed (in Knots) when cruising. The table is formatted as follows: `cruise_TAS_table_by_weight_and_altitude = weight, weight, etc... : temperature, temperature, etc... : altitude, altitude, etc... :: airspeed, airspeed, etc... : airspeed, airspeed, etc... : etc... : etc...` For example: `cruise_TAS_table_by_weight_and_altitude = 4407, 5071 : -10, 0, 10, 20, 30 : 2000, 4000, 6000, 8000, 10000, 12000, 14000, 16000, 18000, 20000 :: 156.00, 159.00, 162.00, 166.00, 169.00, 172.00, 175.00, 179.00, 182.00, 186.00 : 158.00, 161.00, 164.00, 168.00, 171.00, 174.00, 177.00, 181.00, 184.00, 188.00 : 160.00, 163.00, 166.00, 169.00, 173.00, 176.00, 179.00, 183.00, 186.00, 185.00 : 162.00, 165.00, 168.00, 171.00, 175.00, 178.00, 181.00, 185.00, 188.00, 187.00 : etc...`	2D Table	Yes
`cruise_fuel_consumption_table_by_weight_and_altitude`	This is a table that correlates a given weight (in lbs) with the OAT deviation from ISA (in °C) and a given altitude (in ft) to give the fuel consumption (in Gallons / hour) when cruising. The table is formatted as follows: `cruise_fuel_consumption_table_by_weight_and_altitude = weight, weight, etc... : temperature, temperature, etc... : altitude, altitude, etc... :: fuel_gallons, fuel_gallons, etc... : fuel_gallons, fuel_gallons, etc... : etc... : etc...` For example: `cruise_fuel_consumption_table_by_weight_and_altitude = 4407, 5071 : -10, 0, 10, 20, 30 : 2000, 4000, 6000, 8000, 10000, 12000, 14000, 16000, 18000, 20000 :: 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800 : 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800 : 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 13.900 : 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 13.900 : etc...`	2D Table	Yes

cruise_TAS_table_by_weight_and_altitude

This is a table that correlates a given weight (in lbs) with the OAT deviation from ISA (in °C) and a given altitude (in ft) to give the true airspeed (in Knots) when cruising.

The table is formatted as follows:

cruise_TAS_table_by_weight_and_altitude = weight, weight, etc... : temperature, temperature, etc... : altitude, altitude, etc... :: airspeed, airspeed, etc... : airspeed, airspeed, etc... : etc... : etc...

For example:

cruise_TAS_table_by_weight_and_altitude = 4407, 5071 : -10, 0, 10, 20, 30 : 2000, 4000, 6000, 8000, 10000, 12000, 14000, 16000, 18000, 20000 :: 156.00, 159.00, 162.00, 166.00, 169.00, 172.00, 175.00, 179.00, 182.00, 186.00 : 158.00, 161.00, 164.00, 168.00, 171.00, 174.00, 177.00, 181.00, 184.00, 188.00 : 160.00, 163.00, 166.00, 169.00, 173.00, 176.00, 179.00, 183.00, 186.00, 185.00 : 162.00, 165.00, 168.00, 171.00, 175.00, 178.00, 181.00, 185.00, 188.00, 187.00 : etc...

2D Table

Yes

cruise_fuel_consumption_table_by_weight_and_altitude

This is a table that correlates a given weight (in lbs) with the OAT deviation from ISA (in °C) and a given altitude (in ft) to give the fuel consumption (in Gallons / hour) when cruising.

The table is formatted as follows:

cruise_fuel_consumption_table_by_weight_and_altitude = weight, weight, etc... : temperature, temperature, etc... : altitude, altitude, etc... :: fuel_gallons, fuel_gallons, etc... : fuel_gallons, fuel_gallons, etc... : etc... : etc...

For example:

cruise_fuel_consumption_table_by_weight_and_altitude = 4407, 5071 : -10, 0, 10, 20, 30 : 2000, 4000, 6000, 8000, 10000, 12000, 14000, 16000, 18000, 20000 :: 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800 : 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800 : 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 13.900 : 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 14.800, 13.900 : etc...

2D Table

Yes