# flight_performance.cfg<no value>

{{< image-center
    src="images/2_DevMode/simobject_editor/cfg/cfg_tab_20_flightperformance.png"
    alt="The flight_performance.cfg File In The SimObject Editor" >}}

The `flight_performance.cfg` is an *optional* file for aircraft SimObjects, but is not used by any other type of SimObject. This file is used to check the performance characteristics of an aircraft for use with the flight model and for correctly configuring **EFB** flight plans and other (user created) 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 {{< glossterm >}}POH{{< /glossterm >}} or from industrial or academic data) and is currently mainly used by the {{< glossterm >}}EFB{{< /glossterm >}} to generate flight plans within the simulation (the [`[PERFORMANCE_DATA]`](#performance_data) section is the exception, as this is *not* used by the EFB, but *is* used by the simulation for ATC, flightplan, and career missions).

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:

-   [Debug Aircraft Flight Performance](../../../devmode/editors/simobject-editor/debug/debug-aircraft-flight-performance/)

To aid with setting up this file, you can find a page of recommendations and explanations from the following link:

-   [flight_performance.cfg - Setup](../flight-performance/flight_performance.cfg-additional-information/)


### [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.

{{< table-wrapper "150px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="major" />}}`major` | Major CFG file version number, values must be greater than 0. | Integer | Yes |
| {{< anchor id="minor" />}}`minor` | Minor CFG file version number, values must be greater than 0. | Integer | Yes |

{{< /table-wrapper >}}


### [PERFORMANCE_DATA]

This section is used to setup some specific performance value which will be used for *simulation* flightplan calculations - but *not* the EFB flightplans, unlike the other sections on this page - and ATC, as well as some career constraints (see [Mission Solving Constraints](../../careers/general-career-information/general-career-mode-requirements/#mission_solving) for more information). Much of this information can be found online using a resource like [Aircraft Performance Database](https://learningzone.eurocontrol.int/ilp/customs/ATCPFDB/default.aspx?).

{{< table-wrapper "200px" "" "150px" "200px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="TakeOff" />}}`TakeOff` | This hashmap is used to define the takeoff performance parameters. The following keys are available:<span></span>{{< params/smallfont-list >}} - **MaximumTakeOffWeight** - The maximum permitted takeoff weight (in kg).<span></span> - **WakeTurbulenceCategory** - The [ICAO Wake Turbulence Category](https://skybrary.aero/articles/icao-wake-turbulence-category) of the plane. One of either L, M, H, or J.<span></span> - **WakeTurbulenceReCategory** - The [Wake Turbulence Re-categorisation](https://skybrary.aero/articles/recat-wake-turbulence-re-categorisation) of the plane. One of either A,B,C,D,E, or F.<span></span> - **Distance** - The ground roll distance required for the aircraft to achieve takeoff (in Meters)<span></span> - **V2** - The {{< glossterm >}}V2{{< /glossterm >}} for the aircraft takeoff (in {{< glossterm >}}knots{{< /glossterm >}}).{{< /params/smallfont-list >}} | [Hash Map](../cfg-files-general-information/#hash_map) | No<span></span> (All parameters and keys have internal fallbacks) |
| {{< anchor id="Climb.N" />}}`Climb.*N*` | This hashmap is used to define the climb rate for the aircraft between different altitude ranges, each one defined by a different Climb.N parameter. The following keys are available:<span></span>{{< params/smallfont-list >}} - **RateOfClimb** - The rate of climb within the altitude range (in {{< glossterm >}}ft{{< /glossterm >}} / min)<span></span> - **IAS** - The indicated airspeed within the altitude range (in {{< glossterm >}}knots{{< /glossterm >}}). Not required if `Mach` is supplied.<span></span> - **Mach** - The indicated airspeed within the altitude range (in {{< glossterm >}}Mach{{< /glossterm >}}). Not required if `IAS` is supplied.<span></span> - **AltitudeLimit** - the upper altitude limit for the range (in {{< glossterm >}}ft{{< /glossterm >}}).{{< /params/smallfont-list >}}<span></span>Note that *`N`* must always start at zero and increment by 1, and the altitude range is calculated as follows:<span></span>{{< params/smallfont-list >}} - when `*N*`=0 the the range is from 0ft to `AltitudeLimit`.<span></span> - when `*N*`=1 the range is `Climb.0` `AltitudeLimit` to `Climb.1` `AltitudeLimit`.<span></span> - etc...{{< /params/smallfont-list >}} | [Hash Map](../cfg-files-general-information/#hash_map) | No<span></span> (All parameters and keys have internal fallbacks) |
| {{< anchor id="Cruise" />}}`Cruise` | This hashmap is used to define certain parameters for the aircraft when cruising. The following keys are available:<span></span>{{< params/smallfont-list >}} - **TAS** - The true airspeed for the aircraft when at cruise height (in {{< glossterm >}}knots{{< /glossterm >}}). Not required if `Mach` is supplied.<span></span> - **Mach** - The true airspeed for the aircraft when at cruise height (in {{< glossterm >}}Mach{{< /glossterm >}}). Not required if `IAS` is supplied.<span></span> - **Ceiling** - The cruise ceiling altitude (in {{< glossterm >}}ft{{< /glossterm >}})<span></span> - **Range** - The cruise range (in {{< glossterm >}}nm{{< /glossterm >}}){{< /params/smallfont-list >}} | [Hash Map](../cfg-files-general-information/#hash_map) | No<span></span> (All parameters and keys have internal fallbacks) |
| {{< anchor id="Descent.N" />}}`Descent.*N*` | This hashmap is used to define the descent rate for the aircraft between different altitude ranges, each one defined by a different `Descent.*N*` parameter. The following keys are available:<span></span>{{< params/smallfont-list >}} - **RateOfDescent** - The rate of descent within the altitude range (in {{< glossterm >}}ft{{< /glossterm >}} / min)<span></span> - **IAS** - The indicated airspeed within the altitude range (in {{< glossterm >}}knots{{< /glossterm >}}). Not required if `Mach` is supplied.<span></span> - **Mach** - The indicated airspeed within the altitude range (in {{< glossterm >}}Mach{{< /glossterm >}}). Not required if `IAS` is supplied.<span></span> - **AltitudeLimit** - the upper altitude limit for the range (in {{< glossterm >}}ft{{< /glossterm >}}).{{< /params/smallfont-list >}}<span></span>Note that *`N`* must always start at zero and increment by 1, and the altitude range is calculated as follows:<span></span>{{< params/smallfont-list >}} - when `*N*`=0 the the range is from `Descent.0` `AltitudeLimit` to `Descent.1` `AltitudeLimit` (or to 0 if no other `Descent.N` is present)<span></span> - when `*N*`=1 the range is `Descent.1` `AltitudeLimit` to `Descent.2` `AltitudeLimit` (or to 0 if no other `Descent.N` is present)<span></span> - when the last `*N*` is reached, the range is `Descent.[Previous_*N*]` to 0.{{< /params/smallfont-list >}} | [Hash Map](../cfg-files-general-information/#hash_map) | No<span></span> (All parameters and keys have internal fallbacks) |
| {{< anchor id="Approach" />}}`Approach` | This hashmap is used to define the approach performance parameters. The following keys are available:<span></span>{{< params/smallfont-list >}} - **RateOfDescent** - The rate of descent during the approach phase (in {{< glossterm >}}ft{{< /glossterm >}} / min)<span></span> - **IAS** - The indicated airspeed during approach (in {{< glossterm >}}knots{{< /glossterm >}}).<span></span> - **Vmc**- The {{< glossterm >}}VMC{{< /glossterm >}} for the aircraft approach (in {{< glossterm >}}knots{{< /glossterm >}}).{{< /params/smallfont-list >}} | [Hash Map](../cfg-files-general-information/#hash_map) | No<span></span> (All parameters and keys have internal fallbacks) |
| {{< anchor id="Landing" />}}`Landing` | This hashmap is used to define the landing performance parameters. The following keys are available:<span></span>{{< params/smallfont-list >}} - **VAT** - The airspeed ({{< glossterm >}}IAS{{< /glossterm >}}) at runway threshold (in {{< glossterm >}}ft{{< /glossterm >}} / min)<span></span> - **ApproachCategory** - The [Approach Speed Categorisation](https://skybrary.aero/articles/approach-speed-categorisation) of the plane. One of either A,B,C,D,E, or H.<span></span> - **Distance**- The ground roll distance required for the aircraft land (in Meters){{< /params/smallfont-list >}} | [Hash Map](../cfg-files-general-information/#hash_map) | No<span></span> (All parameters and keys have internal fallbacks) |

{{< /table-wrapper >}}


### [AIRCRAFT_CONFIGURATION.N]

This section is intended for storing general aerodynamic characteristics of the aircraft depending on its configuration. This section is indexed, meaning its title must contain an index separated from the section name by a dot. The index must be in the range 0 to 99, there must be at least one such section in the file - ie: `[AIRCRAFT_CONFIGURATION.0]` is mandatory - and indices must be consecutive.

The set of parameters that describe the aircraft configuration (landing gear, flaps, slats, spoilers) are *adaptive*, and their composition and values must correspond to the aircraft design specified in the file [`flight_model.cfg`](../flight_model.cfg/). If a discrepancy is detected when reading this section, then it may be processed as an error.

It should be noted that the [Debug Aircraft Flight Performance Tool](../../devmode/editors/simobject-editor/debug/debug-aircraft-flight-performance/) can be used to exports valid data for this section, depending on the selected aircraft configuration.

The parameters available to this section are as follows:

{{< table-wrapper "250px" "" "150px" "200px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="configuration_name" />}}`configuration_name` | The name of the configuration (as a string). This is purely orientative to help you identify which configuration is being used. | String | Yes<span></span> (Only when more than one configuration exists, otherwise it can be omitted) |
| {{< anchor id="landing_gear_state" />}}`landing_gear_state` | This defines whether the configuration has been created with landing gear down (1, TRUE) or not (0, FALSE). | Boolean | Yes<span></span> (Only when the aircraft has retractable landing gear, otherwise it can be omitted) |
| {{< anchor id="wing_configuration_ID" />}}`wing_configuration_ID` | This tells the configuration which [`[FLAPS.N]`](../flight_model.cfg/#flapsn) setting to use. | Integer | Yes<span></span> (Only when the aircraft has more than 1 wing configuration, otherwise it can be omitted) |
| {{< anchor id="spoilers_angle" />}}`spoilers_angle` | This tells the configuration what spoiler angle to use, in degrees. This cannot be set to more than the values set for [`spoiler_limit`](../flight_model.cfg/#spoiler_limit) or [`air_spoiler_limit`](../flight_model.cfg/#air_spoiler_limit). | Float | Yes<span></span> (Only when the aircraft has spoilers defined, otherwise it can be omitted) |
| {{< anchor id="CL_table_by_Mach_and_AoA" />}}`CL_table_by_Mach_and_AoA` | This is a table that correlates a given speed (in {{< glossterm >}}Mach{{< /glossterm >}}) with a given {{< glossterm >}}AoA{{< /glossterm >}} (in degrees) to give the aircraft lift coefficient (CL). The table is formatted as follows:<span></span>`CL_table_by_Mach_and_AoA = mach, mach, mach, etc... : AoA, AoA, AoA, etc... :: CL, CL, CL, etc... : CL, CL, CL, etc... : CL, CL, CL, etc... : CL, CL, CL, etc...`<span></span>For example:<span></span>`CL_table_by_Mach_and_AoA = 0.000, 0.400 : -5.0, 0.0, 5.0, 10.0, 15.0, 20.0, 25.0 :: -0.19315, 0.41228, 0.94764, 1.35264, 1.53152, 1.10507, 0.81462 : -0.19315, 0.41228, 0.94764, 1.35264, 1.53152, 1.10507, 0.81462` | [2D Table](../cfg-files-general-information/#nd-table) | Yes |
| {{< anchor id="CD_table_by_Mach_and_AoA" />}}`CD_table_by_Mach_and_AoA` | This is a table that correlates a given speed (in {{< glossterm >}}Mach{{< /glossterm >}}) with a given {{< glossterm >}}AoA{{< /glossterm >}} (in degrees) to give the aircraft drag coefficient (CD). The table is formatted as follows:<span></span>`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...`<span></span>For example:<span></span>`CD_table_by_Mach_and_AoA = 0.000, 0.400 : -5.0, 0.0, 5.0, 10.0, 15.0, 20.0, 25.0 :: 0.06102, 0.04087, 0.05659, 0.10079, 0.17588, 0.38295, 0.58907 : 0.06102, 0.04087, 0.05659, 0.10079, 0.17588, 0.38295, 0.58907` | [2D Table](../cfg-files-general-information/#nd-table) | Yes |
| {{< anchor id="stall_AoA_table_by_Mach" />}}`stall_AoA_table_by_Mach` | This is a table that correlates a given speed (in {{< glossterm >}}Mach{{< /glossterm >}}) with a given stall {{< glossterm >}}AoA{{< /glossterm >}} (in degrees).<span></span> **NOTE**: Currently, the dependence of stall AoA on the Mach number is not taken into account in the simulation, but this may change in future updates.<span></span>`stall_AoA_table_by_Mach = mach, mach, mach, etc... :: AoA, AoA, AoA, etc...`<span></span>For example:<span></span>`stall_AoA_table_by_Mach = 0.000, 0.400 :: 14.0, 14.0` | [1D Table](../cfg-files-general-information/#nd-table) | No |

{{< /table-wrapper >}}


### [ENGINE_PERFORMANCE]

This section is intended for storing the aircraft engine characteristics, and as such it can be considered as *optional* given that aircraft like **gliders** do not have an engine. When filling in the data for this section there are few things to note:

-   Currently, this section **does not support more than one engine type** per aircraft.
-   Currently, the [Debug Aircraft Flight Performance Tool](../../devmode/editors/simobject-editor/debug/debug-aircraft-flight-performance/) can export valid data to this section **for turbine engines (jet / turbofan) only**.

As the simulation evolves this section will be improved to cover more engine types and configurations.

The parameters available in this section are as follows:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="number_of_engines" />}}`number_of_engines` | The total number of engines for the aircraft. This is derived from the number of [`Engine.N`](../engines.cfg/#Engine.N) parameters defined in the [engines.cfg](../engines.cfg/). | Integer | Yes |
| {{< anchor id="engine_max_revs" />}}`engine_max_revs` | This sets the maximum revolutions for the engines being tested. For Piston Engines, this is the {{< glossterm >}}rpm{{< /glossterm >}}, and for turbine and turbofan engines, this is a percentage. | Float | Yes |
| {{< anchor id="fuel_density_table" />}}`fuel_density_table` | This list enumerates the densities, in {{< glossterm >}}lbs{{< /glossterm >}} per {{< glossterm >}}Gallon{{< /glossterm >}}, of all fuel types used by the engine(s). These fuel densities can be referenced by the [`[CLIMB_PERFORMANCE.N]`](#climb_performancen), [`[CRUISE_PERFORMANCE.N]`](#cruise_performancen), and [`[CRUISE_PERFORMANCE.N]`](#cruise_performancen) profiles defined in this file. Note that there is no defined order for the densities to be added into this file as the values are referenced by their *index* in the list. ALso note that the parameter is *not* automatically generated by the flight performance tool and must be filled out manually. | [List](../cfg-files-general-information/#list) | No |
| {{< anchor id="engine_net_thrust_table_by_ISA_dev_and_altitude_and_Mach_and_throttle" />}}`engine_net_thrust_table_by_ISA_dev_and_altitude_and_Mach_and_throttle` | This table gives the engine net thrust (in {{< glossterm >}}lbf{{< /glossterm >}}) depending on 4 arguments:<span></span>{{< params/smallfont-list >}} - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - Mach number ({{< glossterm >}}Mach{{< /glossterm >}})<span></span> - Throttle control (unit){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`engine_net_thrust_table_by_ISA_dev_and_altitude_and_Mach_and_throttle = OAT, OAT, etc... : FT, FT, etc... : Mach, Mach, etc... : throttle, throttle, etc... :: lbf, lbf, lbf, etc... : lbf, lbf, lbf, etc.. : etc...`<span></span>**NOTE**: This parameter is only applicable to **turbine engines**. | [4D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="engine_fuel_consumption_table_by_ISA_dev_and_altitude_and_Mach_and_throttle" />}}`engine_fuel_consumption_table_by_ISA_dev_and_altitude_and_Mach_and_throttle` | This table gives the engine fuel consumption (in {{< glossterm >}}lbs{{< /glossterm >}} per hour) depending on 4 arguments:<span></span>{{< params/smallfont-list >}} - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - Mach number ({{< glossterm >}}Mach{{< /glossterm >}})<span></span> - Throttle control (unit){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`engine_fuel_consumption_table_by_ISA_dev_and_altitude_and_Mach_and_throttle = OAT, OAT, etc... : FT, FT, etc... : Mach, Mach, etc... : throttle, throttle, etc... :: lbs, lbs, lbs, etc... : lbs, lbs, lbs, etc.. : etc...`<span></span>**NOTE**: This parameter is only applicable to **turbine engines**. | [4D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="engine_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach_and_throttle" />}}`engine_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach_and_throttle` | This table gives the corrected {{< glossterm >}}N1{{< /glossterm >}} depending on 4 arguments:<span></span>{{< params/smallfont-list >}} - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - Mach number ({{< glossterm >}}Mach{{< /glossterm >}})<span></span> - Throttle control (unit){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`engine_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach_and_throttle = OAT, OAT, etc... : FT, FT, etc... : Mach, Mach, etc... : throttle, throttle, etc... :: n1, n1, n1, etc... : n1, n1, n1, etc.. : etc...`<span></span>**NOTE**: This parameter is only applicable to **turbine engines**. | [4D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="engine_idle_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach" />}}`engine_idle_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach` | This table gives the corrected {{< glossterm >}}N1{{< /glossterm >}} when the throttle position is at it's *minimum*, as defined by the [`min_throttle_limit`](../engines.cfg/#min_throttle_limit) parameter (if the minimum throttle is below 0 then it will be clamped to 0), based on 3 arguments:<span></span>{{< params/smallfont-list >}} - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - Mach number ({{< glossterm >}}Mach{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`engine_idle_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach = OAT, OAT, etc... : FT, FT, etc... : Mach, Mach, etc... :: n1, n1, n1, etc... : n1, n1, n1, etc.. : etc...`<span></span>**NOTE**: This parameter is only applicable to **turbine engines**. | [3D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="engine_idle_descent_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach" />}}`engine_idle_descent_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach` | This table gives the corrected {{< glossterm >}}N1{{< /glossterm >}} when the aircraft is descending and throttle position is at it's *minimum*, as defined by the [`min_throttle_limit`](../engines.cfg/#min_throttle_limit) parameter (if the minimum throttle is below 0 then it will be clamped to 0), based on 3 arguments:<span></span>{{< params/smallfont-list >}} - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - Mach number ({{< glossterm >}}Mach{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`engine_idle_descent_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach = OAT, OAT, etc... : FT, FT, etc... : Mach, Mach, etc... :: n1, n1, n1, etc... : n1, n1, n1, etc.. : etc...`<span></span>**NOTE**: This parameter is only applicable to **turbine engines**. | [3D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="engine_max_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach" />}}`engine_max_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach` | This table gives the corrected {{< glossterm >}}N1{{< /glossterm >}} when the throttle position is at it's *maximum*, based on 3 arguments:<span></span>{{< params/smallfont-list >}} - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - Mach number ({{< glossterm >}}Mach{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`engine_max_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach = OAT, OAT, etc... : FT, FT, etc... : Mach, Mach, etc... :: n1, n1, n1, etc... : n1, n1, n1, etc.. : etc...`<span></span>**NOTE**: This parameter is only applicable to **turbine engines**. | [3D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="engine_climb_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach" />}}`engine_climb_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach` | This table gives the corrected {{< glossterm >}}N1{{< /glossterm >}} when the throttle position is at it's *maximum* and the aircraft is climbing, based on 3 arguments:<span></span>{{< params/smallfont-list >}} - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - Mach number ({{< glossterm >}}Mach{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`engine_climb_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach = OAT, OAT, etc... : FT, FT, etc... : Mach, Mach, etc... :: n1, n1, n1, etc... : n1, n1, n1, etc.. : etc...`<span></span>**NOTE**: This parameter is only applicable to **turbine engines**. | [3D Table](../cfg-files-general-information/#nd-table) | No |

{{< /table-wrapper >}}


### [TAKEOFF_PERFORMANCE]

This section contains tables of data related to the performance when the aircraft is **taking off**. The performance data in this section can be calculated using two different methods:

-   Using the completed distance tables
-   Or using V-tables ({{< glossterm >}}V1{{< /glossterm >}}, {{< glossterm >}}Vr{{< /glossterm >}}, {{< glossterm >}}V2{{< /glossterm >}}) to calculate distance (for more information on these calculations please see here: [Notes On V1, Vr, V2 Computations](../flight-performance/flight_performance.cfg-additional-information/#notes-on-v1-vr-v2-computations))

The distance table parameters that specify **takeoff ground roll distance** and **takeoff total distance** have *priority* in determining these distances for the {{< glossterm >}}EFB{{< /glossterm >}}. If either (or both) of these tables are missing from this section, then the takeoff distances in the EFB will be calculated based on the V-table parameters, using aerodynamic data for the aircraft in the requested [`[AIRCRAFT_CONFIGURATION.N]`](#aircraft_configurationn) and the available maximum thrust of the engines defined in the [`[ENGINE_PERFORMANCE]`](#engine_performance) section. These calculations are performed on the basis of the physical laws of flight dynamics, which describe the acceleration of an aircraft to takeoff speed and its climb to the standard obstacle height (50 feet) under the physical forces acting on the aircraft (ie: weight, lift, drag, thrust, wheel friction). For more information on the takeoff distance calculations, please see here:

-   [Notes On Takeoff Distances](../flight-performance/flight_performance.cfg-additional-information/#notes-on-takeoff-distance)


Available distance table parameters are:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="takeoff_ground_roll_distance_table_by_weight_and_OAT_and_altitude" />}}`takeoff_ground_roll_distance_table_by_weight_and_OAT_and_altitude` | This table gives the take-off ground roll distance (in {{< glossterm >}}ft{{< /glossterm >}}) depending on the following 3 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`takeoff_ground_roll_distance_table_by_weight_and_OAT_and_altitude = weight, weight, etc... : OAT, OAT, etc... : Alt, Alt, etc... :: dist, dist, dist, etc... : dist, dist, dist, etc.. : etc...` | [3D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="takeoff_total_distance_table_by_weight_and_OAT_and_altitude" />}}`takeoff_total_distance_table_by_weight_and_OAT_and_altitude` | This table gives the take-off total distance (in {{< glossterm >}}ft{{< /glossterm >}}) to clear a 50-foot obstacle depending on the following 3 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`takeoff_total_distance_table_by_weight_and_OAT_and_altitude = weight, weight, etc... : OAT, OAT, etc... : Alt, Alt, etc... :: dist, dist, dist, etc... : dist, dist, dist, etc.. : etc...` | [3D Table](../cfg-files-general-information/#nd-table) | No |

{{< /table-wrapper >}}


Available V-table parameters are:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="V1_table_by_flaps_and_weight" />}}`V1_table_by_flaps_and_weight` | The indicated airspeed ({{< glossterm >}}IAS{{< /glossterm >}}, in {{< glossterm >}}knots{{< /glossterm >}}) of decision - go / no go - {{< glossterm >}}V1{{< /glossterm >}} depending on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Wing configuration ID (index of the parameter to use)<span></span> - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`V1_table_by_flaps_and_weight = wing_config, wing_config, etc... : weight, weight, etc... :: IAS, IAS, etc... : IAS, IAS, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="Vr_table_by_flaps_and_weight" />}}`Vr_table_by_flaps_and_weight` | The indicated airspeed ({{< glossterm >}}IAS{{< /glossterm >}}, in {{< glossterm >}}knots{{< /glossterm >}}) of the initial rotation speed ({{< glossterm >}}Vr{{< /glossterm >}}) during takeoff depending on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Wing configuration ID (index of the parameter to use)<span></span> - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`V1_table_by_flaps_and_weight = wing_config, wing_config, etc... : weight, weight, etc... :: IAS, IAS, etc... : IAS, IAS, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="V2_table_by_flaps_and_weight" />}}`V2_table_by_flaps_and_weight` | The indicated airspeed ({{< glossterm >}}IAS{{< /glossterm >}}, in {{< glossterm >}}knots{{< /glossterm >}}) of {{< glossterm >}}V2{{< /glossterm >}} depending on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Wing configuration ID (index of the parameter to use)<span></span> - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`V2_table_by_flaps_and_weight = wing_config, wing_config, etc... : weight, weight, etc... :: IAS, IAS, etc... : IAS, IAS, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="V1_adjustments_table_by_altitude_and_OAT" />}}`V1_adjustments_table_by_altitude_and_OAT` | The adjustment of {{< glossterm >}}V1{{< /glossterm >}} based on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} (°C){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`V1_adjustments_table_by_altitude_and_OAT = alt, alt, etc... : OAT, OAT, etc... :: knots, knots, etc... : knots, knots, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="Vr_adjustments_table_by_altitude_and_OAT" />}}`Vr_adjustments_table_by_altitude_and_OAT` | The adjustment of {{< glossterm >}}Vr{{< /glossterm >}} based on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} (°C){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`Vr_adjustments_table_by_altitude_and_OAT = alt, alt, etc... : OAT, OAT, etc... :: knots, knots, etc... : knots, knots, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="V2_adjustments_table_by_altitude_and_OAT" />}}`V2_adjustments_table_by_altitude_and_OAT` | The adjustment of {{< glossterm >}}V2{{< /glossterm >}} based on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} (°C){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`V2_adjustments_table_by_altitude_and_OAT = alt, alt, etc... : OAT, OAT, etc... :: knots, knots, etc... : knots, knots, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="V1_adjustments_table_by_slope_and_weight" />}}`V1_adjustments_table_by_slope_and_weight` | The adjustment of {{< glossterm >}}V1{{< /glossterm >}} based on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Runway slope (%)<span></span> - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`V1_adjustments_table_by_slope_and_weight = slope, slope, etc... : weight, weight, etc... :: knots, knots, etc... : knots, knots, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="V1_adjustments_table_by_wind_and_weight" />}}`V1_adjustments_table_by_wind_and_weight` | The adjustment of {{< glossterm >}}V1{{< /glossterm >}} based on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Headwind ({{< glossterm >}}knots{{< /glossterm >}})<span></span> - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`V1_adjustments_table_by_wind_and_weight = wind, wind, etc... : weight, weight, etc... :: knots, knots, etc... : knots, knots, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |

{{< /table-wrapper >}}


### [CLIMB_PERFORMANCE.N]

This *optional* section contains tables of data related to the aircraft **climb** performance. This section is indexed, where each indexed section is an individual climb profile. Indices must be in the range 0 to 99, and must also be consecutive.

{{< callout context="note" title="NOTE" icon="outline/bulb" >}}

When this section is created by [Debug Aircraft Flight Performance](../../devmode/editors/simobject-editor/debug/debug-aircraft-flight-performance/) tool, it is only a **template** that is created, and you will need to fill in the required values yourself based on information from the aircraft manufacturer.

{{< /callout >}}


The available parameters in this section are:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="profile_name-CLIMB_PERFORMANCEN" />}}`profile_name` | The name of the climb profile. This is purely for organisational purposes and is not used in the simulation. | String | No |
| {{< anchor id="fuel_type_idx-CLIMB_PERFORMANCEN" />}}`fuel_type_idx` | This value determines the density of the fuel used by the engine when using this profile. The given value is an index into the list defined by the [`fuel_density_table`](#fuel_density_table) parameter, such that an index of 0 refers to the first density in the list, an index of 1 refers to the second density, etc...<span></span>Default value is 0. | Integer | No |
| {{< anchor id="IAS_below_transition-CLIMB_PERFORMANCEN" />}}`IAS_below_transition` | Sets the target {{< glossterm >}}IAS{{< /glossterm >}} when below the transition altitude, in {{< glossterm >}}knots{{< /glossterm >}}. Value must be greater than 0.<span></span>Default value is 0 (ie: the parameter is ignored). | Float | No |
| {{< anchor id="IAS_above_transition-CLIMB_PERFORMANCEN" />}}`IAS_above_transition` | Sets the target {{< glossterm >}}IAS{{< /glossterm >}} when above the transition altitude, in {{< glossterm >}}knots{{< /glossterm >}}. Value must be greater than 0.<span></span>Default value is 0 (ie: the parameter is ignored). | Float | No |
| {{< anchor id="Mach-CLIMB_PERFORMANCEN" />}}`Mach` | The target {{< glossterm >}}Mach{{< /glossterm >}} number. Value must be greater than 0.<span></span>Default value is 0 (ie: the parameter is ignored). | Float | No |
| {{< anchor id="time_to_climb_table_by_initial_weight_and_altitude" />}}`time_to_climb_table_by_initial_weight_and_altitude` | Table defining the total time (in seconds) to climb from sea level to a given altitude, depending on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft initial climb weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - Pressure altitude to climb ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`time_to_climb_table_by_initial_weight_and_altitude = weight, weight, etc... : alt, alt, etc... :: time, time, etc... : time, time, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="fuel_to_climb_table_by_initial_weight_and_altitude" />}}`fuel_to_climb_table_by_initial_weight_and_altitude` | Table defining the fuel consumed (in {{< glossterm >}}Gallons{{< /glossterm >}}) when climbing from sea level to a given altitude, depending on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft initial climb weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - Pressure altitude to climb ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`fuel_to_climb_table_by_initial_weight_and_altitude = weight, weight, etc... : alt, alt, etc... :: amount, amount, etc... : amount, amount, etc... : etc...` | [2D Table](../cfg-files-general-information/#nd-table) | No |

{{< /table-wrapper >}}


### [CRUISE_PERFORMANCE.N]

This *optional* section contains parameters and tables of data related to the aircraft **cruise** performance. This section is indexed, where each indexed section is an individual cruise profile. Indices must be in the range 0 to 99, and must also be consecutive.

{{< callout context="note" title="NOTE" icon="outline/bulb" >}}

When this section is created by [Debug Aircraft Flight Performance](../../devmode/editors/simobject-editor/debug/debug-aircraft-flight-performance/) tool, it is only a **template** that is created, and you will need to fill in the required values yourself based on information from the aircraft manufacturer.

{{< /callout >}}


The available parameters in this section are:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="profile_name-CRUISE_PERFORMANCEN" />}}`profile_name` | The name of the cruise profile. This is purely for organisational purposes and is not used in the simulation. | String | No |
| {{< anchor id="fuel_type_idx-CRUISE_PERFORMANCEN" />}}`fuel_type_idx` | This value determines the density of the fuel used by the engine when using this profile. The given value is an index into the list defined by the [`fuel_density_table`](#fuel_density_table) parameter, such that an index of 0 refers to the first density in the list, an index of 1 refers to the second density, etc...<span></span>Default value is 0. | Integer | No |
| {{< anchor id="Mach-CRUISE_PERFORMANCEN" />}}`Mach` | Target {{< glossterm >}}Mach{{< /glossterm >}} number. | Float | No |
| {{< anchor id="cruise_TAS_table_by_weight_and_ISA_dev_and_altitude" />}}`cruise_TAS_table_by_weight_and_ISA_dev_and_altitude` | This table gives the cruise true airspeed ({{< glossterm >}}TAS,{{< /glossterm >}} in {{< glossterm >}}knots{{< /glossterm >}}) based on the following 3 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`cruise_TAS_table_by_weight_and_ISA_dev_and_altitude = weight, weight, etc... : OAT, OAT, etc... : Alt, Alt, etc... :: TAS, TAS, TAS, etc... : TAS, TAS, TAS, etc.. : etc...` | [3D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="cruise_fuel_consumption_table_by_weight_and_ISA_dev_and_altitude" />}}`cruise_fuel_consumption_table_by_weight_and_ISA_dev_and_altitude` | This table gives the fuel consumption (in {{< glossterm >}}Gallons{{< /glossterm >}} per hour) when cruising based on the following 3 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`cruise_fuel_consumption_table_by_weight_and_ISA_dev_and_altitude = weight, weight, etc... : OAT, OAT, etc... : Alt, Alt, etc... :: gph, gph, gph, etc... : gph, gph, gph, etc.. : etc...` | [3D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="cruise_max_altitude_table_by_weight_and_ISA_dev-CRUISE_PERFORMANCEN" />}}`cruise_max_altitude_table_by_weight_and_ISA_dev` | This table gives the maximum operating pressure altitude (in {{< glossterm >}}ft{{< /glossterm >}}) when cruising based on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`cruise_fuel_consumption_table_by_weight_and_ISA_dev_and_altitude = weight, weight, etc... : OAT, OAT, etc... :: alt, alt, alt, etc... : alt, alt, alt, etc.. : etc...`<span></span>Note that the maximum cruise altitude defined by this table applies *only when using this cruise profile*. If a global maximum cruise altitude table is defined in the [`[AIRCRAFT_LIMITS]`](#aircraft_limits) section, then this table will override the global one when this profile is used. | [2D Table](../cfg-files-general-information/#nd-table) | No |

{{< /table-wrapper >}}


### [DESCENT_PERFORMANCE.N]

This *optional* section contains parameters related to the aircraft **descent** performance. This section is indexed, where each indexed section is an individual descent profile. Indices must be in the range 0 to 99, and must also be consecutive.

{{< callout context="note" title="NOTE" icon="outline/bulb" >}}

When this section is created by [Debug Aircraft Flight Performance](../../devmode/editors/simobject-editor/debug/debug-aircraft-flight-performance/) tool, it is only a **template** that is created, and you will need to fill in the required values yourself based on information from the aircraft manufacturer.

{{< /callout >}}


The available parameters in this section are:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="profile_name-DESCENT_PERFORMANCEN" />}}`profile_name` | The name of the descent profile. This is purely for organisational purposes and is not used in the simulation. | String | No |
| {{< anchor id="fuel_type_idx-DESCENT_PERFORMANCEN" />}}`fuel_type_idx` | This value determines the density of the fuel used by the engine when using this profile. The given value is an index into the list defined by the [`fuel_density_table`](#fuel_density_table) parameter, such that an index of 0 refers to the first density in the list, an index of 1 refers to the second density, etc...<span></span>Default value is 0. | Integer | No |
| {{< anchor id="IAS_below_transition-DESCENT_PERFORMANCEN" />}}`IAS_below_transition` | Sets the target {{< glossterm >}}IAS{{< /glossterm >}} when below the transition altitude, in {{< glossterm >}}knots{{< /glossterm >}}. Value must be greater than 0.<span></span>Default value is 0 (ie: the parameter is ignored). | Float | No |
| {{< anchor id="IAS_above_transition-DESCENT_PERFORMANCEN" />}}`IAS_above_transition` | Sets the target {{< glossterm >}}IAS{{< /glossterm >}} when above the transition altitude, in {{< glossterm >}}knots{{< /glossterm >}}. Value must be greater than 0.<span></span>Default value is 0 (ie: the parameter is ignored). | Float | No |
| {{< anchor id="Mach-DESCENT_PERFORMANCEN" />}}`Mach` | The target {{< glossterm >}}Mach{{< /glossterm >}} number. Value must be greater than 0.<span></span>Default value is 0 (ie: the parameter is ignored). | Float | No |
| {{< anchor id="average_descent_rate" />}}`average_descent_rate` | The target average descent rate, in {{< glossterm >}}ft{{< /glossterm >}} per minute.<span></span>Default value is 0 (ie: the parameter is ignored). | Float | No |
| {{< anchor id="fuel_to_descent_table_by_cruise_altitude" />}}`fuel_to_descent_table_by_cruise_altitude` | Defgines the total amount of fuel consumed (in {{< glossterm >}}Gallons{{< /glossterm >}}) in descent from a given altitude to sea level depending on 1 argument:<span></span>{{< params/smallfont-list >}} - cruise pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`fuel_to_descent_table_by_cruise_altitude = alt, alt, etc... :: gal, gal, gal, etc...` | [1D Table](../cfg-files-general-information/#nd-table) | No |

{{< /table-wrapper >}}


### [LANDING_PERFORMANCE]

This *mandatory* section contains tables of data related to the aircraft **landing** performance. You can find more information about the calculations involved in landing performance calculations here:

-   [Notes On Landing Distances](../flight-performance/flight_performance.cfg-additional-information/#notes-on-landing-distances)


Available parameters are:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="landing_ground_roll_distance_table_by_weight_and_OAT_and_altitude" />}}`landing_ground_roll_distance_table_by_weight_and_OAT_and_altitude` | This is a table that gives the landing roll distance (in {{< glossterm >}}ft{{< /glossterm >}}) based on the following 3 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft weight (in {{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} (in °C)<span></span> - Pressure altitude (in {{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`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...` | [3D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="landing_total_distance_table_by_weight_and_OAT_and_altitude" />}}`landing_total_distance_table_by_weight_and_OAT_and_altitude` | This is a table that gives the total landing distance (in {{< glossterm >}}ft{{< /glossterm >}}) required to clear a 50{{< glossterm >}}ft{{< /glossterm >}} obstacle based on the following 3 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft weight (in {{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} (in °C)<span></span> - Pressure altitude (in {{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`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...` | [3D Table](../cfg-files-general-information/#nd-table) | Yes |

{{< /table-wrapper >}}


### [AIRCRAFT_LOADING]

This *optional* section contains parameters related to the aircraft **loading** performance. If the section is included then the `passenger_capacity` parameter is required.

The available parameters in this section are:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="fuel_capacity" />}}`fuel_capacity` | The fuel system capacity, in {{< glossterm >}}Gallons{{< /glossterm >}}. | Float | No |
| {{< anchor id="cargo_capacity" />}}`cargo_capacity` | The aircraft cargo capacity, in {{< glossterm >}}lbs{{< /glossterm >}}. | Float | No |
| {{< anchor id="passenger_capacity" />}}`passenger_capacity` | The maximum number of passengers the aircraft can hold. | Integer | Yes |

{{< /table-wrapper >}}


### [AIRCRAFT_LIMITS]

This *optional* section contains parameters related to the aircraft **limits**. The available parameters in this section are:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="cruise_max_altitude_table_by_weight_and_ISA_dev-AIRCRAFT_LIMITS" />}}`cruise_max_altitude_table_by_weight_and_ISA_dev` | This table gives the maximum operating pressure altitude (in {{< glossterm >}}ft{{< /glossterm >}}) when cruising based on the following 2 arguments:<span></span>{{< params/smallfont-list >}} - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`cruise_fuel_consumption_table_by_weight_and_ISA_dev_and_altitude = weight, weight, etc... : OAT, OAT, etc... :: alt, alt, alt, etc... : alt, alt, alt, etc.. : etc...`<span></span>Note that the maximum cruise altitude defined by this table applies globally in all scenarios except when using a cruise profile ([`[CRUISE_PERFORMANCE.N]`](#cruise_performancen)) that defines its own maximum cruise altitude table - in that case the maximum cruise altitude defined by the profile takes precedence. | [2D Table](../cfg-files-general-information/#nd-table) | No |

{{< /table-wrapper >}}


### [COST_INDICES]

This *optional* section contains parameters related to the aircraft **cost indices** ({{< glossterm >}}CI{{< /glossterm >}}).

{{< callout context="note" title="NOTE" icon="outline/bulb" >}}

When this section is created by [Debug Aircraft Flight Performance](../../devmode/editors/simobject-editor/debug/debug-aircraft-flight-performance/) tool, it is only a **template** that is created, and you will need to fill in the required values yourself based on information from the aircraft manufacturer.

{{< /callout >}}


The available parameters in this section are:

{{< table-wrapper "300px" "" "100px" "100px" >}}

| Parameter | Description | Type | Required |
|---|---|---|:---:|
| {{< anchor id="climb_econ_IAS_table_uses_TOC_weight_and_ISA_dev" />}}`climb_econ_IAS_table_uses_TOC_weight_and_ISA_dev` | This parameter is used to select how the weight and {{< glossterm >}}ISA{{< /glossterm >}} deviation arguments in the [climb econ IAS table](#climb_econ_IAS_table_by_cost_index_and_weight_and_ISA_dev_and_cruise_altitude) will be interpreted:<span></span>{{< params/smallfont-list >}} - When set to 0 the weight and temperature deviation values in this table are specified for the **bottom of climb** (takeoff).<span></span> - When set to 1, the climb econ {{< glossterm >}}IAS{{< /glossterm >}} computation will assume that the specified weight and temperature deviation in this table are the ones expected when the aircraft is at **top of climb** ({{< glossterm >}}ToC{{< /glossterm >}}).{{< /params/smallfont-list >}} | Boolean | No |
| {{< anchor id="climb_econ_Mach_table_uses_TOC_weight_and_ISA_dev" />}}`climb_econ_Mach_table_uses_TOC_weight_and_ISA_dev` | This parameter is used to select how the weight and {{< glossterm >}}ISA{{< /glossterm >}} deviation arguments in the [climb econ mach table](#climb_econ_Mach_table_by_cost_index_and_weight_and_ISA_dev_and_cruise_altitude) will be interpreted<span></span>{{< params/smallfont-list >}} - When set to 0 the weight and temperature deviation values in this table are specified for the **bottom of climb** (takeoff).<span></span> - When set to 1, the climb econ {{< glossterm >}}Mach{{< /glossterm >}} number computation will assume that the specified weight and temperature deviation in this table are the ones expected when the aircraft is at **top of climb** ({{< glossterm >}}ToC{{< /glossterm >}}).{{< /params/smallfont-list >}} | Boolean | No |
| {{< anchor id="climb_econ_IAS_table_by_cost_index_and_weight_and_ISA_dev_and_cruise_altitude" />}}`climb_econ_IAS_table_by_cost_index_and_weight_and_ISA_dev_and_cruise_altitude` | This table gives the target climb econ (minimum cost speed) indicated airspeed ({{< glossterm >}}IAS{{< /glossterm >}} in {{< glossterm >}}knots{{< /glossterm >}}) depending on 4 arguments:<span></span>{{< params/smallfont-list >}} - Cost index ({{< glossterm >}}CI{{< /glossterm >}}, unitless float)<span></span> - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}}) - either takeoff or {{< glossterm >}}ToC{{< /glossterm >}}, depending on the [climb econ IAS flag](#climb_econ_IAS_table_uses_TOC_weight_and_ISA_dev).<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C) - either takeoff or {{< glossterm >}}ToC{{< /glossterm >}}, depending on the [climb econ IAS flag](#climb_econ_IAS_table_uses_TOC_weight_and_ISA_dev).<span></span> - Cruise pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`climb_econ_IAS_table_by_cost_index_and_weight_and_ISA_dev_and_cruise_altitude = CI, CI, etc... : weight, weight, etc... : OAT, OAT, etc... : alt, alt, etc... :: IAS, IAS, IAS, etc... : IAS, IAS, IAS, etc.. : etc...` | [4D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="climb_econ_Mach_table_by_cost_index_and_weight_and_ISA_dev_and_cruise_altitude" />}}`climb_econ_Mach_table_by_cost_index_and_weight_and_ISA_dev_and_cruise_altitude` | This table gives the target climb econ (minimum cost speed) {{< glossterm >}}Mach{{< /glossterm >}} number depending on 4 arguments:<span></span>{{< params/smallfont-list >}} - Cost index (integer)<span></span> - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}}) - either takeoff or {{< glossterm >}}ToC{{< /glossterm >}}, depending on the [climb econ IAS flag](#climb_econ_IAS_table_uses_TOC_weight_and_ISA_dev).<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C) - either takeoff or {{< glossterm >}}ToC{{< /glossterm >}}, depending on the [climb econ IAS flag](#climb_econ_IAS_table_uses_TOC_weight_and_ISA_dev).<span></span> - Cruise pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`climb_econ_IAS_table_by_cost_index_and_weight_and_ISA_dev_and_cruise_altitude = CI, CI, etc... : weight, weight, etc... : OAT, OAT, etc... : alt, alt, etc... :: mach, mach, mach, etc... : mach, mach, mach, etc.. : etc...` | [4D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="cruise_econ_Mach_table_by_cost_index_and_weight_and_ISA_dev_and_altitude" />}}`cruise_econ_Mach_table_by_cost_index_and_weight_and_ISA_dev_and_altitude` | This table gives the target cruise econ (minimum cost speed) {{< glossterm >}}Mach{{< /glossterm >}} number depending on 4 arguments:<span></span>{{< params/smallfont-list >}} - Cost index (integer)<span></span> - Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - Cruise pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`cruise_econ_Mach_table_by_cost_index_and_weight_and_ISA_dev_and_altitude = CI, CI, etc... : weight, weight, etc... : OAT, OAT, etc... : alt, alt, etc... :: mach, mach, mach, etc... : mach, mach, mach, etc.. : etc...` | [4D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="descent_econ_IAS_table_by_cost_index_and_TOD_weight_and_TOD_ISA_dev_and_TOD_altitude" />}}`descent_econ_IAS_table_by_cost_index_and_TOD_weight_and_TOD_ISA_dev_and_TOD_altitude` | This table gives the descent econ (minimum cost speed) indicated airspeed ({{< glossterm >}}IAS{{< /glossterm >}} in {{< glossterm >}}knots{{< /glossterm >}}) depending on 4 arguments:<span></span>{{< params/smallfont-list >}} - Cost index ({{< glossterm >}}CI{{< /glossterm >}}, unitless float)<span></span> - {{< glossterm >}}ToD{{< /glossterm >}} Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}ToD{{< /glossterm >}} {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - {{< glossterm >}}ToD{{< /glossterm >}} Cruise pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`climb_econ_IAS_table_by_cost_index_and_weight_and_ISA_dev_and_cruise_altitude = CI, CI, etc... : weight, weight, etc... : OAT, OAT, etc... : alt, alt, etc... :: IAS, IAS, IAS, etc... : IAS, IAS, IAS, etc.. : etc...` | [4D Table](../cfg-files-general-information/#nd-table) | No |
| {{< anchor id="descent_econ_Mach_table_by_cost_index_and_TOD_weight_and_TOD_ISA_dev_and_TOD_altitude" />}}`descent_econ_Mach_table_by_cost_index_and_TOD_weight_and_TOD_ISA_dev_and_TOD_altitude` | This table gives the descent econ (minimum cost speed) {{< glossterm >}}Mach{{< /glossterm >}} number depending on 4 arguments:<span></span>{{< params/smallfont-list >}} - Cost index (integer)<span></span> - {{< glossterm >}}ToD{{< /glossterm >}} Aircraft weight ({{< glossterm >}}lbs{{< /glossterm >}})<span></span> - {{< glossterm >}}ToD{{< /glossterm >}} {{< glossterm >}}OAT{{< /glossterm >}} deviation from {{< glossterm >}}ISA{{< /glossterm >}} (°C)<span></span> - {{< glossterm >}}ToD{{< /glossterm >}} Cruise pressure altitude ({{< glossterm >}}ft{{< /glossterm >}}){{< /params/smallfont-list >}}<span></span>The table is formatted as follows:<span></span>`descent_econ_Mach_table_by_cost_index_and_TOD_weight_and_TOD_ISA_dev_and_TOD_altitude = CI, CI, etc... : weight, weight, etc... : OAT, OAT, etc... : alt, alt, etc... :: mach, mach, mach, etc... : mach, mach, mach, etc.. : etc...` | [4D Table](../cfg-files-general-information/#nd-table) | No |

{{< /table-wrapper >}}