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 (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 POH or from industrial or academic data) and is currently only used by the EFB to generate flight plans within the simulation.

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:

 

 

[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_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. 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 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:

 

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.

 String Yes
(Only when more than one configuration exists, otherwise it can be omitted)
landing_gear_state

This defines whether the configuration has been created with landing gear down (1, TRUE) or not (0, FALSE).

 Boolean Yes
(Only when the aircraft has retractable landing gear, otherwise it can be omitted)
wing_configuration_ID

This tells the configuration which [FLAPS.N] setting to use.

 Integer Yes
(Only when the aircraft has more than 1 wing configuration, otherwise it can be omitted)
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 or air_spoiler_limit.

 Float Yes
(Only when the aircraft has spoilers defined, otherwise it can be omitted)
CL_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 lift coefficient (CL). The table is formatted as follows:

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...

For example:

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
 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, 0.400 : -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 Yes
stall_AoA_table_by_Mach

This is a table that correlates a given speed (in Mach) with a given stall AoA (in degrees).
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. 

stall_AoA_table_by_Mach = mach, mach, mach, etc... :: AoA, AoA, AoA, etc...

For example:

stall_AoA_table_by_Mach = 0.000, 0.400 :: 14.0, 14.0
 1D Table Yes

 

 

[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, this section can only be used for turbine engines.
  • Currently, the Debug Aircraft Flight Performance Tool 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:

 

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. Integer 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.

 Float Yes
engine_net_thrust_table_by_ISA_dev_and_altitude_and_Mach_and_throttle

This table gives the engine net thrust (in lbf) depending on 4 arguments:

  1. OAT deviation from ISA (°C)
  2. Pressure altitude (ft)
  3. Mach number (Mach)
  4. Throttle control (unit)

The table is formatted as follows:

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...
 4D Table Yes
engine_fuel_consumption_table_by_ISA_dev_and_altitude_and_Mach_and_throttle

This table gives the engine fuel consumption (in lbs per hour) depending on 4 arguments:

  1. OAT deviation from ISA (°C)
  2. Pressure altitude (ft)
  3. Mach number (Mach)
  4. Throttle control (unit)

The table is formatted as follows:

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...
 4D Table Yes
engine_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach_and_throttle

This table gives the corrected N1 depending on 4 arguments:

  1. OAT deviation from ISA (°C)
  2. Pressure altitude (ft)
  3. Mach number (Mach)
  4. Throttle control (unit)

The table is formatted as follows:

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...
 4D Table Yes
engine_idle_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach

This table gives the corrected N1 when the throttle position is at it's minimum, as defined by the min_throttle_limit parameter (if the minimum throttle is below 0 then it will be clamped to 0), based on 3 arguments:

  1. OAT deviation from ISA (°C)
  2. Pressure altitude (ft)
  3. Mach number (Mach)

The table is formatted as follows:

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...
 3D Table Yes
engine_idle_descent_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach

This table gives the corrected N1 when the aircraft is descending and throttle position is at it's minimum, as defined by the min_throttle_limit parameter (if the minimum throttle is below 0 then it will be clamped to 0), based on 3 arguments:

  1. OAT deviation from ISA (°C)
  2. Pressure altitude (ft)
  3. Mach number (Mach)

The table is formatted as follows:

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...
 3D Table Yes
engine_max_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach

This table gives the corrected N1 when the throttle position is at it's maximum, based on 3 arguments:

  1. OAT deviation from ISA (°C)
  2. Pressure altitude (ft)
  3. Mach number (Mach)

The table is formatted as follows:

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...
 3D Table Yes
engine_climb_corrected_N1_table_by_ISA_dev_and_altitude_and_Mach

This table gives the corrected N1 when the throttle position is at it's maximum and the aircraft is climbing, based on 3 arguments:

  1. OAT deviation from ISA (°C)
  2. Pressure altitude (ft)
  3. Mach number (Mach)

The table is formatted as follows:

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...
 3D Table Yes

 

 

[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:

The distance table parameters that specify takeoff ground roll distance and takeoff total distance have priority in determining these distances for the EFB. 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] and the available maximum thrust of the engines defined in the [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:

 

Available distance table parameters are:

 

Parameter Description Type Required
takeoff_ground_roll_distance_table_by_weight_and_OAT_and_altitude

This table gives the take-off ground roll distance (in ft) depending on the following 3 arguments:

  1. Aircraft weight (lbs)
  2. OAT (°C)
  3. Pressure altitude (ft)

The table is formatted as follows:

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 Yes
takeoff_total_distance_table_by_weight_and_OAT_and_altitude

This table gives the take-off total distance (in ft) to clear a 50-foot obstacle depending on the following 3 arguments:

  1. Aircraft weight (lbs)
  2. OAT (°C)
  3. Pressure altitude (ft)

The table is formatted as follows:

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 Yes

 

Available V-table parameters are:

 

Parameter Description Type Required
V1_table_by_flaps_and_weight

The indicated airspeed (IAS, in Knots) of decision - go / no go - V1 depending on the following 2 arguments:

  1. Wing configuration ID (index of the FLAPS.N parameter to use)
  2. Aircraft weight (lbs)

The table is formatted as follows:

V1_table_by_flaps_and_weight = wing_config, wing_config, etc... : weight, weight, etc... :: IAS, IAS, etc... : IAS, IAS, etc... : etc...
 2D Table Yes
Vr_table_by_flaps_and_weight

The indicated airspeed (IAS, in Knots) of the initial rotation speed (Vr) during takeoff depending on the following 2 arguments:

  1. Wing configuration ID (index of the FLAPS.N parameter to use)
  2. Aircraft weight (lbs)

The table is formatted as follows:

V1_table_by_flaps_and_weight = wing_config, wing_config, etc... : weight, weight, etc... :: IAS, IAS, etc... : IAS, IAS, etc... : etc...
 2D Table Yes
V2_table_by_flaps_and_weight

The indicated airspeed (IAS, in Knots) of V2 depending on the following 2 arguments:

  1. Wing configuration ID (index of the FLAPS.N parameter to use)
  2. Aircraft weight (lbs)

The table is formatted as follows:

V2_table_by_flaps_and_weight = wing_config, wing_config, etc... : weight, weight, etc... :: IAS, IAS, etc... : IAS, IAS, etc... : etc...
 2D Table Yes
V1_adjustments_table_by_altitude_and_OAT

The adjustment of V1 based on the following 2 arguments:

  1. Pressure altitude (ft)
  2. OAT (°C)

The table is formatted as follows:

V1_adjustments_table_by_altitude_and_OAT = alt, alt, etc... : OAT, OAT, etc... :: knots, knots, etc... : knots, knots, etc... : etc...
 2D Table Yes
Vr_adjustments_table_by_altitude_and_OAT

The adjustment of Vr based on the following 2 arguments:

  1. Pressure altitude (ft)
  2. OAT (°C)

The table is formatted as follows:

Vr_adjustments_table_by_altitude_and_OAT = alt, alt, etc... : OAT, OAT, etc... :: knots, knots, etc... : knots, knots, etc... : etc...
 2D Table Yes
V2_adjustments_table_by_altitude_and_OAT

The adjustment of V2 based on the following 2 arguments:

  1. Pressure altitude (ft)
  2. OAT (°C)

The table is formatted as follows:

V2_adjustments_table_by_altitude_and_OAT = alt, alt, etc... : OAT, OAT, etc... :: knots, knots, etc... : knots, knots, etc... : etc...
 2D Table Yes
V1_adjustments_table_by_slope_and_weight

The adjustment of V1 based on the following 2 arguments:

  1. Runway slope (%)
  2. Aircraft weight (lbs)

The table is formatted as follows:

V1_adjustments_table_by_slope_and_weight = slope, slope, etc... : weight, weight, etc... :: knots, knots, etc... : knots, knots, etc... : etc...
 2D Table Yes
V1_adjustments_table_by_wind_and_weight

The adjustment of V1 based on the following 2 arguments:

  1. Headwind (Knots)
  2. Aircraft weight (lbs)

The table is formatted as follows:

V1_adjustments_table_by_wind_and_weight = wind, wind, etc... : weight, weight, etc... :: knots, knots, etc... : knots, knots, etc... : etc...
 2D Table Yes

 

 

[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.

NOTE: When this section is created by 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.

 

The available parameters in this section are:

 

Parameter Description Type Required
profile_name The name of the climb profile. This is purely for organisational purposes and is not used in the simulation. String No
IAS_below_transition

Sets the target IAS when below the transition altitude, in Knots. Value must be greater than 0.

Default value is 0 (ie: the parameter is ignored).

 Float No
IAS_above_transition

Sets the target IAS when above the transition altitude, in Knots. Value must be greater than 0.

Default value is 0 (ie: the parameter is ignored).

 Float No
Mach

The target Mach number. Value must be greater than 0.

Default value is 0 (ie: the parameter is ignored).

 Float No
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:

  1. Aircraft initial climb weight (lbs)
  2. Pressure altitude to climb (ft)

The table is formatted as follows:

time_to_climb_table_by_initial_weight_and_altitude = weight, weight, etc... : alt, alt, etc... :: time, time, etc... : time, time, etc... : etc...
 2D Table No
fuel_to_climb_table_by_initial_weight_and_altitude

Table defining the fuel consumed (in Gallons) when climbing from sea level to a given altitude, depending on the following 2 arguments:

  1. Aircraft initial climb weight (lbs)
  2. Pressure altitude to climb (ft)

The table is formatted as follows:

fuel_to_climb_table_by_initial_weight_and_altitude = weight, weight, etc... : alt, alt, etc... :: amount, amount, etc... : amount, amount, etc... : etc...
 2D Table No

 

 

[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.

NOTE: When this section is created by 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.

 

The available parameters in this section are:

 

Parameter Description Type Required
profile_name The name of the cruise profile. This is purely for organisational purposes and is not used in the simulation. String No
cruise_Mach Target Mach number. Float No
cruise_TAS_table_by_weight_and_ISA_dev_and_altitude

This table gives the cruise true airspeed (TAS in Knots) based on the following 3 arguments:

  1. Aircraft weight (lbs)
  2. OAT deviation from ISA (°C)
  3. Pressure altitude (ft)

The table is formatted as follows:

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 No
cruise_fuel_consumption_table_by_weight_and_ISA_dev_and_altitude

This table gives the fuel consumption (in Gallons per hour) when cruising based on the following 3 arguments:

  1. Aircraft weight (lbs)
  2. OAT deviation from ISA (°C)
  3. Pressure altitude (ft)

The table is formatted as follows:

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 No
cruise_max_altitude_table_by_weight_and_ISA_dev

This table gives the maximum operating pressure altitude (in ft) when cruising based on the following 2 arguments:

  1. Aircraft weight (lbs)
  2. OAT deviation from ISA (°C)

The table is formatted as follows:

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...
 2D Table No

 

 

[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.

NOTE: When this section is created by 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.

 

The available parameters in this section are:

 

Parameter Description Type Required
profile_name The name of the descent profile. This is purely for organisational purposes and is not used in the simulation. String No
IAS_below_transition

Sets the target IAS when below the transition altitude, in Knots. Value must be greater than 0.

Default value is 0 (ie: the parameter is ignored).

 Float No
IAS_above_transition

Sets the target IAS when above the transition altitude, in Knots. Value must be greater than 0.

Default value is 0 (ie: the parameter is ignored).

 Float No
Mach

The target Mach number. Value must be greater than 0.

Default value is 0 (ie: the parameter is ignored).

 Float No
average_descent_rate

The target average descent rate, in ft per minute.

Default value is 0 (ie: the parameter is ignored).

 Float No
fuel_to_descent_table_by_cruise_altitude

Defgines the total amount of fuel consumed (in Gallons) in descent from a given altitude to sea level depending on 1 argument:

  1. cruise pressure altitude (ft)

The table is formatted as follows:

fuel_to_descent_table_by_cruise_altitude = alt, alt, etc... :: gal, gal, gal, etc...
 1D Table No

 

 

[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:

 

Available parameters are:

 

Parameter Description Type Required
landing_ground_roll_distance_table_by_weight_and_OAT_and_altitude

This is a table that gives the landing roll distance (in ft) based on the following 3 arguments:

  1. Aircraft weight (in lbs)
  2. OAT (in °C)
  3. Pressure altitude (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...
 3D Table Yes
landing_total_distance_table_by_weight_and_OAT_and_altitude

This is a table that gives the total landing distance (in ft) required to clear a 50ft obstacle based on the following 3 arguments:

  1. Aircraft weight (in lbs)
  2. OAT (in °C)
  3. Pressure altitude (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...
 3D Table Yes

 

 

[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:

 

Parameter Description Type Required
fuel_capacity The fuel system capacity, in Gallons. Float No
cargo_capacity The aircraft cargo capacity, in lbs. Float No
passenger_capacity The maximum number of passengers the aircraft can hold. Integer Yes

 

 

[COST_INDICES]

This optional section contains parameters related to the aircraft cost indices (CI).

NOTE: When this section is created by 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.

 

The available parameters in this section are:

 

Parameter Description Type Required
climb_econ_IAS_table_uses_TOC_weight_and_ISA_dev

This parameter is used to select how the weight and ISA deviation arguments in the climb econ IAS table will be interpreted:

  • When set to 0 the weight and temperature deviation values in this table are specified for the bottom of climb (takeoff).
  • When set to 1, the climb econ IAS 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 (ToC).
 Boolean No
climb_econ_Mach_table_uses_TOC_weight_and_ISA_dev

This parameter is used to select how the weight and ISA deviation arguments in the climb econ mach table will be interpreted

  • When set to 0 the weight and temperature deviation values in this table are specified for the bottom of climb (takeoff).
  • When set to 1, the climb econ Mach 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 (ToC).
 Boolean No
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 (IAS in Knots) depending on 4 arguments:

  1. Cost index (CI, unitless float)
  2. Aircraft weight (lbs) - either takeoff or ToC, depending on the climb econ IAS flag.
  3. OAT deviation from ISA (°C) - either takeoff or ToC, depending on the climb econ IAS flag.
  4. Cruise pressure altitude (ft)

The table is formatted as follows:

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 No
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) Mach number depending on 4 arguments:

  1. Cost index (integer)
  2. Aircraft weight (lbs) - either takeoff or ToC, depending on the climb econ IAS flag.
  3. OAT deviation from ISA (°C) - either takeoff or ToC, depending on the climb econ IAS flag.
  4. Cruise pressure altitude (ft)

The table is formatted as follows:

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 No
cruise_econ_Mach_table_by_cost_index_and_weight_and_ISA_dev_and_altitude

This table gives the target cruise econ (minimum cost speed) Mach number depending on 4 arguments:

  1. Cost index (integer)
  2. Aircraft weight (lbs)
  3. OAT deviation from ISA (°C)
  4. Cruise pressure altitude (ft)

The table is formatted as follows:

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 No
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 (IAS in Knots) depending on 4 arguments:

  1. Cost index (CI, unitless float)
  2. ToD Aircraft weight (lbs)
  3. ToD OAT deviation from ISA (°C)
  4. ToD Cruise pressure altitude (ft)

The table is formatted as follows:

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 No
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) Mach number depending on 4 arguments:

  1. Cost index (integer)
  2. ToD Aircraft weight (lbs)
  3. ToD OAT deviation from ISA (°C)
  4. ToD Cruise pressure altitude (ft)

The table is formatted as follows:

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 No

 

 

 

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