Class: AeroMath
A utility class for working with common aeronautical constants and calculations.
Constructors
constructor
• new AeroMath(): AeroMath
Returns
Properties
DENSITY_SEA_LEVEL_ISA
▪ Static Readonly DENSITY_SEA_LEVEL_ISA: number
The density of air at sea level under ISA conditions, in kilograms per cubic meter.
Defined in
src/sdk/math/AeroMath.ts:18
GAMMA_AIR
▪ Static Readonly GAMMA_AIR: 1.4
Approximate value of the adiabatic index of air near room temperature.
Defined in
src/sdk/math/AeroMath.ts:12
R
▪ Static Readonly R: 8.314462618153
The ideal gas constant, in units of joules per mole per kelvin.
Defined in
src/sdk/math/AeroMath.ts:6
R_AIR
▪ Static Readonly R_AIR: 287.057
The specific gas constant of dry air, in units of joules per kilogram per kelvin.
Defined in
src/sdk/math/AeroMath.ts:9
SOUND_SPEED_SEA_LEVEL_ISA
▪ Static Readonly SOUND_SPEED_SEA_LEVEL_ISA: 340.2964
The speed of sound in air at sea level under ISA conditions, in meters per second.
Defined in
src/sdk/math/AeroMath.ts:15
drag
▪ Static drag: (cd: number, area: number, density: number, flowSpeed: number) => number(cd: number, area: number, dynamicPressure: number) => number = AeroMath.flowForceFromCoef
Type declaration
▸ (cd, area, density, flowSpeed): number
Calculates drag force, in newtons, given certain parameters.
Parameters
| Name | Type | Description |
|---|---|---|
cd | number | The drag coefficient. |
area | number | The wing area, in meters squared. |
density | number | The flow density, in kilograms per cubic meter. |
flowSpeed | number | The flow speed, in meters per second. |
Returns
number
The drag force, in newtons, given the specified parameters.
▸ (cd, area, dynamicPressure): number
Calculates drag force, in newtons, given certain parameters.
Parameters
| Name | Type | Description |
|---|---|---|
cd | number | The drag coefficient. |
area | number | The wing area, in meters squared. |
dynamicPressure | number | The flow dynamic pressure, in hectopascals. |
Returns
number
The drag force, in newtons, given the specified parameters.
Defined in
src/sdk/math/AeroMath.ts:688
dragCoefficient
▪ Static dragCoefficient: (drag: number, area: number, density: number, flowSpeed: number) => number(drag: number, area: number, dynamicPressure: number) => number = AeroMath.flowCoefFromForce
Type declaration
▸ (drag, area, density, flowSpeed): number
Calculates the drag coefficient given certain parameters.
Parameters
| Name | Type | Description |
|---|---|---|
drag | number | - |
area | number | The wing area, in meters squared. |
density | number | The flow density, in kilograms per cubic meter. |
flowSpeed | number | The flow speed, in meters per second. |
Returns
number
The drag coefficient given the specified parameters.
▸ (drag, area, dynamicPressure): number
Calculates the drag coefficient given certain parameters.
Parameters
| Name | Type | Description |
|---|---|---|
drag | number | The drag force, in newtons. |
area | number | The wing area, in meters squared. |
dynamicPressure | number | The flow dynamic pressure, in hectopascals. |
Returns
number
The drag coefficient given the specified parameters.
Defined in
src/sdk/math/AeroMath.ts:668
lift
▪ Static lift: (cl: number, area: number, density: number, flowSpeed: number) => number(cl: number, area: number, dynamicPressure: number) => number = AeroMath.flowForceFromCoef
Type declaration
▸ (cl, area, density, flowSpeed): number
Calculates lift force, in newtons, given certain parameters.
Parameters
| Name | Type | Description |
|---|---|---|
cl | number | The lift coefficient. |
area | number | The wing area, in meters squared. |
density | number | The flow density, in kilograms per cubic meter. |
flowSpeed | number | The flow speed, in meters per second. |
Returns
number
The lift force, in newtons, given the specified parameters.
▸ (cl, area, dynamicPressure): number
Calculates lift force, in newtons, given certain parameters.
Parameters
| Name | Type | Description |
|---|---|---|
cl | number | The lift coefficient. |
area | number | The wing area, in meters squared. |
dynamicPressure | number | The flow dynamic pressure, in hectopascals. |
Returns
number
The lift force, in newtons, given the specified parameters.
Defined in
src/sdk/math/AeroMath.ts:648
liftCoefficient
▪ Static liftCoefficient: (lift: number, area: number, density: number, flowSpeed: number) => number(lift: number, area: number, dynamicPressure: number) => number = AeroMath.flowCoefFromForce
Type declaration
▸ (lift, area, density, flowSpeed): number
Calculates the lift coefficient given certain parameters.
Parameters
| Name | Type | Description |
|---|---|---|
lift | number | The lift force, in newtons. |
area | number | The wing area, in meters squared. |
density | number | The flow density, in kilograms per cubic meter. |
flowSpeed | number | The flow speed, in meters per second. |
Returns
number
The lift coefficient given the specified parameters.
▸ (lift, area, dynamicPressure): number
Calculates the lift coefficient given certain parameters.
Parameters
| Name | Type | Description |
|---|---|---|
lift | number | The lift force, in newtons. |
area | number | The wing area, in meters squared. |
dynamicPressure | number | The flow dynamic pressure, in hectopascals. |
Returns
number
The lift coefficient given the specified parameters.
Defined in
src/sdk/math/AeroMath.ts:628
Methods
altitudeOffsetBaroPressure
▸ altitudeOffsetBaroPressure(offset): number
Gets the altimeter barometric pressure setting, in hectopascals, to obtain a given offset to apply to pressure altitude to yield indicated altitude.
Parameters
| Name | Type | Description |
|---|---|---|
offset | number | The altitude offset, in meters, for which to get the barometric pressure setting. |
Returns
number
The altimeter barometric pressure setting, in hectopascals, to obtain the specified offset to apply to pressure altitude to yield indicated altitude.
Defined in
src/sdk/math/AeroMath.ts:278
baroPressureAltitudeOffset
▸ baroPressureAltitudeOffset(baro): number
Gets the offset to apply to pressure altitude, in meters, to obtain indicated altitude for a given altimeter barometric pressure setting.
Parameters
| Name | Type | Description |
|---|---|---|
baro | number | The barometic pressure setting, in hectopascals, for which to get the offset. |
Returns
number
The offset to apply to pressure altitude, in meters, to obtain indicated altitude for the specified altimeter barometric pressure setting.
Defined in
src/sdk/math/AeroMath.ts:267
casToEas
▸ casToEas(cas, pressure): number
Converts calibrated airspeed (CAS) to equivalent airspeed (EAS). The conversion is only valid for subsonic speeds.
Parameters
| Name | Type | Description |
|---|---|---|
cas | number | The calibrated airspeed to convert, in meters per second. |
pressure | number | The ambient static pressure, in hectopascals. |
Returns
number
The equivalent airspeed, in meters per second, corresponding to the specified calibrated airspeed at the specified ambient static pressure.
Defined in
src/sdk/math/AeroMath.ts:552
casToEasIsa
▸ casToEasIsa(cas, altitude): number
Converts calibrated airspeed (CAS) to equivalent airspeed (EAS) under ISA conditions. The conversion is only valid for subsonic speeds.
Parameters
| Name | Type | Description |
|---|---|---|
cas | number | The calibrated airspeed to convert, in meters per second. |
altitude | number | The pressure altitude, in meters above MSL. |
Returns
number
The equivalent airspeed, in meters per second, corresponding to the specified calibrated airspeed at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:568
casToMach
▸ casToMach(cas, pressure): number
Converts calibrated airspeed (CAS) to mach number. The conversion is only valid for subsonic speeds.
Parameters
| Name | Type | Description |
|---|---|---|
cas | number | The calibrated airspeed to convert, in meters per second. |
pressure | number | The ambient static pressure, in hectopascals. |
Returns
number
The mach number equivalent of the specified calibrated airspeed at the specified static pressure.
Defined in
src/sdk/math/AeroMath.ts:355
casToMachIsa
▸ casToMachIsa(cas, altitude): number
Converts calibrated airspeed (CAS) to mach number under ISA conditions. The conversion is only valid for subsonic speeds.
Parameters
| Name | Type | Description |
|---|---|---|
cas | number | The calibrated airspeed to convert, in meters per second. |
altitude | number | The pressure altitude, in meters above MSL. |
Returns
number
The mach number equivalent of the specified calibrated airspeed at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:374
casToTas
▸ casToTas(cas, pressure, temperature): number
Converts calibrated airspeed (CAS) to true airspeed (TAS).
Parameters
| Name | Type | Description |
|---|---|---|
cas | number | The calibrated airspeed to convert, in meters per second. |
pressure | number | The ambient static pressure, in hectopascals. |
temperature | number | The ambient static temperature, in degrees Celsius. |
Returns
number
The true airspeed equivalent, in meters per second, of the specified calibrated airspeed at the specified ambient pressure and temperature.
Defined in
src/sdk/math/AeroMath.ts:415
casToTasIsa
▸ casToTasIsa(cas, altitude, deltaIsa?): number
Converts calibrated airspeed (CAS) to true airspeed (TAS) under ISA conditions.
Parameters
| Name | Type | Default value | Description |
|---|---|---|---|
cas | number | undefined | The calibrated airspeed to convert, in meters per second. |
altitude | number | undefined | The pressure altitude, in meters above MSL. |
deltaIsa | number | 0 | The deviation from ISA temperature, in degrees Celsius. Defaults to 0. |
Returns
number
The true airspeed equivalent, in meters per second, of the specified calibrated airspeed at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:427
densityAir
▸ densityAir(pressure, temperature): number
Gets the density of air, in kilograms per cubic meter, given static pressure and temperature.
Parameters
| Name | Type | Description |
|---|---|---|
pressure | number | The static pressure, in hectopascals. |
temperature | number | The temperature, in degrees Celsius. |
Returns
number
The density of air, in kilograms per cubic meter, with the specified static pressure and temperature.
Defined in
src/sdk/math/AeroMath.ts:38
easToCas
▸ easToCas(eas, pressure): number
Converts equivalent airspeed (EAS) to calibrated airspeed (CAS). The conversion is only valid for subsonic speeds.
Parameters
| Name | Type | Description |
|---|---|---|
eas | number | The equivalent airspeed to convert, in meters per second. |
pressure | number | The ambient static pressure, in hectopascals. |
Returns
number
The calibrated airspeed, in meters per second, corresponding to the specified equivalent airspeed at the specified ambient static pressure.
Defined in
src/sdk/math/AeroMath.ts:579
easToCasIsa
▸ easToCasIsa(eas, altitude): number
Converts equivalent airspeed (EAS) to calibrated airspeed (CAS) under ISA conditions. The conversion is only valid for subsonic speeds.
Parameters
| Name | Type | Description |
|---|---|---|
eas | number | The equivalent airspeed to convert, in meters per second. |
altitude | number | The pressure altitude, in meters above MSL. |
Returns
number
The calibrated airspeed, in meters per second, corresponding to the specified equivalent airspeed at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:591
easToMach
▸ easToMach(eas, pressure): number
Converts equivalent airspeed (EAS) to mach number.
Parameters
| Name | Type | Description |
|---|---|---|
eas | number | The equivalent airspeed to convert, in meters per second. |
pressure | number | The ambient static pressure, in hectopascals. |
Returns
number
The mach number corresponding to the specified equivalent airspeed at the specified ambient static pressure.
Defined in
src/sdk/math/AeroMath.ts:530
easToMachIsa
▸ easToMachIsa(eas, altitude): number
Converts equivalent airspeed (EAS) to mach number under ISA conditions.
Parameters
| Name | Type | Description |
|---|---|---|
eas | number | The equivalent airspeed to convert, in meters per second. |
altitude | number | The pressure altitude, in meters above MSL. |
Returns
number
The mach number corresponding to the specified equivalent airspeed at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:541
easToTas
▸ easToTas(eas, density): number
Converts equivalent airspeed (EAS) to true airspeed (TAS).
Parameters
| Name | Type | Description |
|---|---|---|
eas | number | The equivalent airspeed to convert. |
density | number | The ambient density, in kilograms per cubic meter. |
Returns
number
The true airspeed corresponding to the specified equivalent airspeed at the specified ambient density. The true airspeed is expressed in the same units as the equivalent airspeed.
Defined in
src/sdk/math/AeroMath.ts:485
easToTasIsa
▸ easToTasIsa(eas, altitude, deltaIsa?): number
Converts equivalent airspeed (EAS) to true airspeed (TAS) under ISA conditions.
Parameters
| Name | Type | Default value | Description |
|---|---|---|---|
eas | number | undefined | The equivalent airspeed to convert. |
altitude | number | undefined | The pressure altitude, in meters above MSL. |
deltaIsa | number | 0 | The deviation from ISA temperature, in degrees Celsius. Defaults to 0. |
Returns
number
The true airspeed corresponding to the specified equivalent airspeed at the specified pressure altitude under ISA conditions. The true airspeed is expressed in the same units as the equivalent airspeed.
Defined in
src/sdk/math/AeroMath.ts:497
isaAltitude
▸ isaAltitude(pressure): number
Gets the pressure altitude, in meters above MSL, corresponding to a given ISA pressure. The supported pressure altitude range is from -610 to 80000 meters above MSL. This method will return -610 meters for all pressures above the pressure at -610 meters, and 80000 meters for all pressures below the pressure at 80000 meters.
Parameters
| Name | Type | Description |
|---|---|---|
pressure | number | The ISA pressure for which to get the altitude, in hectopascals. |
Returns
number
The pressure altitude, in meters above MSL, corresponding to the specified ISA pressure.
Defined in
src/sdk/math/AeroMath.ts:185
isaDensity
▸ isaDensity(altitude, deltaIsa?): number
Gets the ISA density, in kilograms per cubic meter, at a given pressure altitude. The supported pressure altitude range is from -610 to 80000 meters above MSL. This method will return the density at -610 meters for all altitudes below this range, and the density at 80000 meters for all altitudes above this range.
Parameters
| Name | Type | Default value | Description |
|---|---|---|---|
altitude | number | undefined | The pressure altitude, in meters above MSL. |
deltaIsa | number | 0 | The deviation from ISA temperature, in degrees Celsius. Defaults to 0. |
Returns
number
The ISA density, in kilograms per cubic meter, for the specified pressure altitude.
Defined in
src/sdk/math/AeroMath.ts:246
isaPressure
▸ isaPressure(altitude): number
Gets the ISA pressure, in hectopascals, at a given pressure altitude. The supported pressure altitude range is from -610 to 80000 meters above MSL. This method will return the pressure at -610 meters for all altitudes below this range, and the pressure at 80000 meters for all altitudes above this range.
Parameters
| Name | Type | Description |
|---|---|---|
altitude | number | The pressure altitude, in meters above MSL. |
Returns
number
The ISA pressure, in hectopascals, for the specified pressure altitude.
Defined in
src/sdk/math/AeroMath.ts:125
isaTemperature
▸ isaTemperature(altitude): number
Gets the ISA temperature, in degrees Celsius, at a given pressure altitude. The supported pressure altitude range is from -610 to 80000 meters above MSL. This method will return the temperature at -610 meters for all altitudes below this range, and the temperature at 80000 meters for all altitudes above this range.
Parameters
| Name | Type | Description |
|---|---|---|
altitude | number | The pressure altitude, in meters above MSL. |
Returns
number
The ISA temperature, in degrees Celsius, for the specified pressure altitude.
Defined in
src/sdk/math/AeroMath.ts:99
machToCas
▸ machToCas(mach, pressure): number
Converts mach number to calibrated airspeed (CAS). The conversion is only valid for subsonic speeds.
Parameters
| Name | Type | Description |
|---|---|---|
mach | number | The mach number to convert. |
pressure | number | The ambient static pressure, in hectopascals. |
Returns
number
The calibrated airspeed equivalent in meters per second of the specified mach number at the specified static pressure.
Defined in
src/sdk/math/AeroMath.ts:385
machToCasIsa
▸ machToCasIsa(mach, altitude): number
Converts mach number to calibrated airspeed (CAS) under ISA conditions. The conversion is only valid for subsonic speeds.
Parameters
| Name | Type | Description |
|---|---|---|
mach | number | The mach number to convert. |
altitude | number | The pressure altitude, in meters above MSL. |
Returns
number
The calibrated airspeed equivalent in meters per second of the specified mach number at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:403
machToEas
▸ machToEas(mach, pressure): number
Converts mach number to equivalent airspeed (EAS).
Parameters
| Name | Type | Description |
|---|---|---|
mach | number | The mach number to convert. |
pressure | number | The ambient static pressure, in hectopascals. |
Returns
number
The equivalent airspeed, in meters per second, corresponding to the specified mach number at the specified ambient static pressure.
Defined in
src/sdk/math/AeroMath.ts:508
machToEasIsa
▸ machToEasIsa(mach, altitude): number
Converts mach number to equivalent airspeed (EAS) under ISA conditions.
Parameters
| Name | Type | Description |
|---|---|---|
mach | number | The mach number to convert. |
altitude | number | The pressure altitude, in meters above MSL. |
Returns
number
The equivalent airspeed, in meters per second, corresponding to the specified mach number at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:519
machToTas
▸ machToTas(mach, soundSpeed): number
Converts mach number to true airspeed (TAS).
Parameters
| Name | Type | Description |
|---|---|---|
mach | number | The mach number to convert. |
soundSpeed | number | The speed of sound. |
Returns
number
The true airspeed equivalent of the specified mach number, in the same units as soundSpeed.
Defined in
src/sdk/math/AeroMath.ts:333
machToTasIsa
▸ machToTasIsa(mach, altitude, deltaIsa?): number
Converts mach number to true airspeed (TAS), in meters per second, under ISA conditions.
Parameters
| Name | Type | Default value | Description |
|---|---|---|---|
mach | number | undefined | The mach number to convert. |
altitude | number | undefined | The pressure altitude, in meters above MSL. |
deltaIsa | number | 0 | The deviation from ISA temperature, in degrees Celsius. Defaults to 0. |
Returns
number
The true airspeed equivalent, in meters per second, of the specified mach number at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:345
pressureAir
▸ pressureAir(temperature, density): number
Gets the static pressure of air, in hectopascals, given temperature and density.
Parameters
| Name | Type | Description |
|---|---|---|
temperature | number | The temperature, in degrees Celsius. |
density | number | The density, in kilograms per cubic meter. |
Returns
number
The static pressure of air, in hectopascals, with the specified temperature and density.
Defined in
src/sdk/math/AeroMath.ts:28
soundSpeedAir
▸ soundSpeedAir(temperature): number
Gets the speed of sound in air, in meters per second, for a given temperature.
Parameters
| Name | Type | Description |
|---|---|---|
temperature | number | The temperature, in degrees Celsius. |
Returns
number
The speed of sound in air, in meters per second, for the given temperature.
Defined in
src/sdk/math/AeroMath.ts:59
soundSpeedIsa
▸ soundSpeedIsa(altitude, deltaIsa?): number
Gets the speed of sound, in meters per second, at a given pressure altitude under ISA conditions.
Parameters
| Name | Type | Default value | Description |
|---|---|---|---|
altitude | number | undefined | The pressure altitude, in meters above MSL. |
deltaIsa | number | 0 | The deviation from ISA temperature, in degrees Celsius. Defaults to 0. |
Returns
number
The speed of sound, in meters per second, at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:256
tasToCas
▸ tasToCas(tas, pressure, temperature): number
Converts true airspeed (TAS) to calibrated airspeed (CAS).
Parameters
| Name | Type | Description |
|---|---|---|
tas | number | The true airspeed to convert, in meters per second. |
pressure | number | The ambient static pressure, in hectopascals. |
temperature | number | The ambient static temperature, in degrees Celsius. |
Returns
number
The calibrated airspeed equivalent, in meters per second, of the specified true airspeed at the specified ambient pressure and temperature.
Defined in
src/sdk/math/AeroMath.ts:439
tasToCasIsa
▸ tasToCasIsa(tas, altitude, deltaIsa?): number
Converts true airspeed (TAS) to calibrated airspeed (CAS) under ISA conditions.
Parameters
| Name | Type | Default value | Description |
|---|---|---|---|
tas | number | undefined | The true airspeed to convert, in meters per second. |
altitude | number | undefined | The pressure altitude, in meters above MSL. |
deltaIsa | number | 0 | The deviation from ISA temperature, in degrees Celsius. Defaults to 0. |
Returns
number
The calibrated airspeed equivalent, in meters per second, of the specified true airspeed at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:451
tasToEas
▸ tasToEas(tas, density): number
Converts true airspeed (TAS) to equivalent airspeed (EAS).
Parameters
| Name | Type | Description |
|---|---|---|
tas | number | The true airspeed to convert. |
density | number | The ambient density, in kilograms per cubic meter. |
Returns
number
The equivalent airspeed corresponding to the specified true airspeed at the specified ambient density. The equivalent airspeed is expressed in the same units as the true airspeed.
Defined in
src/sdk/math/AeroMath.ts:462
tasToEasIsa
▸ tasToEasIsa(tas, altitude, deltaIsa?): number
Converts true airspeed (TAS) to equivalent airspeed (EAS) under ISA conditions.
Parameters
| Name | Type | Default value | Description |
|---|---|---|---|
tas | number | undefined | The true airspeed to convert. |
altitude | number | undefined | The pressure altitude, in meters above MSL. |
deltaIsa | number | 0 | The deviation from ISA temperature, in degrees Celsius. Defaults to 0. |
Returns
number
The equivalent airspeed corresponding to the specified true airspeed at the specified pressure altitude under ISA conditions. The equivalent airspeed is expressed in the same units as the true airspeed.
Defined in
src/sdk/math/AeroMath.ts:474
tasToMach
▸ tasToMach(tas, soundSpeed): number
Converts true airspeed (TAS) to mach number.
Parameters
| Name | Type | Description |
|---|---|---|
tas | number | The true airspeed to convert, in the same units as soundSpeed. |
soundSpeed | number | The speed of sound, in the same units as tas. |
Returns
number
The mach number equivalent of the specified true airspeed.
Defined in
src/sdk/math/AeroMath.ts:311
tasToMachIsa
▸ tasToMachIsa(tas, altitude, deltaIsa?): number
Converts true airspeed (TAS) to mach number under ISA conditions.
Parameters
| Name | Type | Default value | Description |
|---|---|---|---|
tas | number | undefined | The true airspeed to convert, in meters per second. |
altitude | number | undefined | The pressure altitude, in meters above MSL. |
deltaIsa | number | 0 | The deviation from ISA temperature, in degrees Celsius. Defaults to 0. |
Returns
number
The mach number equivalent of the specified true airspeed at the specified pressure altitude under ISA conditions.
Defined in
src/sdk/math/AeroMath.ts:323
temperatureAir
▸ temperatureAir(pressure, density): number
Gets the temperature of air, in degrees Celsius, given static pressure and density.
Parameters
| Name | Type | Description |
|---|---|---|
pressure | number | The static pressure, in hectopascals. |
density | number | The density, in kilograms per cubic meter. |
Returns
number
The temperature of air, in degrees Celsius, with the specified static pressure and temperature.
Defined in
src/sdk/math/AeroMath.ts:48
totalPressureRatioAir
▸ totalPressureRatioAir(mach): number
Gets the ratio of total pressure to static pressure for a given mach number in a subsonic compressible airflow.
Parameters
| Name | Type | Description |
|---|---|---|
mach | number | The mach number. |
Returns
number
The ratio of total pressure to static pressure for the specific mach number.
Defined in
src/sdk/math/AeroMath.ts:73
totalTemperatureRatioAir
▸ totalTemperatureRatioAir(mach, recovery?): number
Gets the ratio of total air temperature to static air temperature for a given mach number.
Parameters
| Name | Type | Default value | Description |
|---|---|---|---|
mach | number | undefined | The mach number. |
recovery | number | 1 | The recovery factor. This is a value in the range [0, 1] representing the fraction of the kinetic energy of the airflow that is converted to heat. Defaults to 1. |
Returns
number
The ratio of total air temperature to static air temperature for the specified mach number.
Defined in
src/sdk/math/AeroMath.ts:86