Class: AeroMath

Defined in: src/sdk/math/AeroMath.ts:4

A utility class for working with common aeronautical constants and calculations.

Constructors

Constructor

new AeroMath(): AeroMath

Returns

AeroMath

Properties

DENSITY_SEA_LEVEL_ISA

readonly static DENSITY_SEA_LEVEL_ISA: number

Defined in: src/sdk/math/AeroMath.ts:18

The density of air at sea level under ISA conditions, in kilograms per cubic meter.

---

drag()

static drag: {(cd, area, density, flowSpeed): number; (cd, area, dynamicPressure): number; } = AeroMath.flowForceFromCoef

Defined in: src/sdk/math/AeroMath.ts:688

Call Signature

(cd, area, density, flowSpeed): number

Calculates drag force, in newtons, given certain parameters.

Parameters

Parameter	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.

Call Signature

(cd, area, dynamicPressure): number

Calculates drag force, in newtons, given certain parameters.

Parameters

Parameter	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.

---

dragCoefficient()

static dragCoefficient: {(drag, area, density, flowSpeed): number; (drag, area, dynamicPressure): number; } = AeroMath.flowCoefFromForce

Defined in: src/sdk/math/AeroMath.ts:668

Call Signature

(drag, area, density, flowSpeed): number

Calculates the drag coefficient given certain parameters.

Parameters

Parameter	Type	Description
drag	number	The drag 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 drag coefficient given the specified parameters.

Call Signature

(drag, area, dynamicPressure): number

Calculates the drag coefficient given certain parameters.

Parameters

Parameter	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.

---

GAMMA_AIR

readonly static GAMMA_AIR: 1.4 = 1.4

Defined in: src/sdk/math/AeroMath.ts:12

Approximate value of the adiabatic index of air near room temperature.

---

lift()

static lift: {(cl, area, density, flowSpeed): number; (cl, area, dynamicPressure): number; } = AeroMath.flowForceFromCoef

Defined in: src/sdk/math/AeroMath.ts:648

Call Signature

(cl, area, density, flowSpeed): number

Calculates lift force, in newtons, given certain parameters.

Parameters

Parameter	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.

Call Signature

(cl, area, dynamicPressure): number

Calculates lift force, in newtons, given certain parameters.

Parameters

Parameter	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.

---

liftCoefficient()

static liftCoefficient: {(lift, area, density, flowSpeed): number; (lift, area, dynamicPressure): number; } = AeroMath.flowCoefFromForce

Defined in: src/sdk/math/AeroMath.ts:628

Call Signature

(lift, area, density, flowSpeed): number

Calculates the lift coefficient given certain parameters.

Parameters

Parameter	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.

Call Signature

(lift, area, dynamicPressure): number

Calculates the lift coefficient given certain parameters.

Parameters

Parameter	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.

---

R

readonly static R: 8.314462618153 = 8.314462618153

Defined in: src/sdk/math/AeroMath.ts:6

The ideal gas constant, in units of joules per mole per kelvin.

---

R_AIR

readonly static R_AIR: 287.057 = 287.057

Defined in: src/sdk/math/AeroMath.ts:9

The specific gas constant of dry air, in units of joules per kilogram per kelvin.

---

SOUND_SPEED_SEA_LEVEL_ISA

readonly static SOUND_SPEED_SEA_LEVEL_ISA: 340.2964 = 340.2964

Defined in: src/sdk/math/AeroMath.ts:15

The speed of sound in air at sea level under ISA conditions, in meters per second.

Methods

altitudeOffsetBaroPressure()

static altitudeOffsetBaroPressure(offset): number

Defined in: src/sdk/math/AeroMath.ts:278

Gets the altimeter barometric pressure setting, in hectopascals, to obtain a given offset to apply to pressure altitude to yield indicated altitude.

Parameters

Parameter	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.

---

baroPressureAltitudeOffset()

static baroPressureAltitudeOffset(baro): number

Defined in: src/sdk/math/AeroMath.ts:267

Gets the offset to apply to pressure altitude, in meters, to obtain indicated altitude for a given altimeter barometric pressure setting.

Parameters

Parameter	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.

---

casToEas()

static casToEas(cas, pressure): number

Defined in: src/sdk/math/AeroMath.ts:552

Converts calibrated airspeed (CAS) to equivalent airspeed (EAS). The conversion is only valid for subsonic speeds.

Parameters

Parameter	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.

---

casToEasIsa()

static casToEasIsa(cas, altitude): number

Defined in: src/sdk/math/AeroMath.ts:568

Converts calibrated airspeed (CAS) to equivalent airspeed (EAS) under ISA conditions. The conversion is only valid for subsonic speeds.

Parameters

Parameter	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.

---

casToMach()

static casToMach(cas, pressure): number

Defined in: src/sdk/math/AeroMath.ts:355

Converts calibrated airspeed (CAS) to mach number. The conversion is only valid for subsonic speeds.

Parameters

Parameter	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.

---

casToMachIsa()

static casToMachIsa(cas, altitude): number

Defined in: src/sdk/math/AeroMath.ts:374

Converts calibrated airspeed (CAS) to mach number under ISA conditions. The conversion is only valid for subsonic speeds.

Parameters

Parameter	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.

---

casToTas()

static casToTas(cas, pressure, temperature): number

Defined in: src/sdk/math/AeroMath.ts:415

Converts calibrated airspeed (CAS) to true airspeed (TAS).

Parameters

Parameter	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.

---

casToTasIsa()

static casToTasIsa(cas, altitude, deltaIsa): number

Defined in: src/sdk/math/AeroMath.ts:427

Converts calibrated airspeed (CAS) to true airspeed (TAS) under ISA conditions.

Parameters

Parameter	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.

---

densityAir()

static densityAir(pressure, temperature): number

Defined in: src/sdk/math/AeroMath.ts:38

Gets the density of air, in kilograms per cubic meter, given static pressure and temperature.

Parameters

Parameter	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.

---

easToCas()

static easToCas(eas, pressure): number

Defined in: src/sdk/math/AeroMath.ts:579

Converts equivalent airspeed (EAS) to calibrated airspeed (CAS). The conversion is only valid for subsonic speeds.

Parameters

Parameter	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.

---

easToCasIsa()

static easToCasIsa(eas, altitude): number

Defined in: src/sdk/math/AeroMath.ts:591

Converts equivalent airspeed (EAS) to calibrated airspeed (CAS) under ISA conditions. The conversion is only valid for subsonic speeds.

Parameters

Parameter	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.

---

easToMach()

static easToMach(eas, pressure): number

Defined in: src/sdk/math/AeroMath.ts:530

Converts equivalent airspeed (EAS) to mach number.

Parameters

Parameter	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.

---

easToMachIsa()

static easToMachIsa(eas, altitude): number

Defined in: src/sdk/math/AeroMath.ts:541

Converts equivalent airspeed (EAS) to mach number under ISA conditions.

Parameters

Parameter	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.

---

easToTas()

static easToTas(eas, density): number

Defined in: src/sdk/math/AeroMath.ts:485

Converts equivalent airspeed (EAS) to true airspeed (TAS).

Parameters

Parameter	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.

---

easToTasIsa()

static easToTasIsa(eas, altitude, deltaIsa): number

Defined in: src/sdk/math/AeroMath.ts:497

Converts equivalent airspeed (EAS) to true airspeed (TAS) under ISA conditions.

Parameters

Parameter	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.

---

isaAltitude()

static isaAltitude(pressure): number

Defined in: src/sdk/math/AeroMath.ts:185

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

Parameter	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.

---

isaDensity()

static isaDensity(altitude, deltaIsa): number

Defined in: src/sdk/math/AeroMath.ts:246

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

Parameter	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.

---

isaPressure()

static isaPressure(altitude): number

Defined in: src/sdk/math/AeroMath.ts:125

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

Parameter	Type	Description
altitude	number	The pressure altitude, in meters above MSL.

Returns

number

The ISA pressure, in hectopascals, for the specified pressure altitude.

---

isaTemperature()

static isaTemperature(altitude): number

Defined in: src/sdk/math/AeroMath.ts:99

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

Parameter	Type	Description
altitude	number	The pressure altitude, in meters above MSL.

Returns

number

The ISA temperature, in degrees Celsius, for the specified pressure altitude.

---

machToCas()

static machToCas(mach, pressure): number

Defined in: src/sdk/math/AeroMath.ts:385

Converts mach number to calibrated airspeed (CAS). The conversion is only valid for subsonic speeds.

Parameters

Parameter	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.

---

machToCasIsa()

static machToCasIsa(mach, altitude): number

Defined in: src/sdk/math/AeroMath.ts:403

Converts mach number to calibrated airspeed (CAS) under ISA conditions. The conversion is only valid for subsonic speeds.

Parameters

Parameter	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.

---

machToEas()

static machToEas(mach, pressure): number

Defined in: src/sdk/math/AeroMath.ts:508

Converts mach number to equivalent airspeed (EAS).

Parameters

Parameter	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.

---

machToEasIsa()

static machToEasIsa(mach, altitude): number

Defined in: src/sdk/math/AeroMath.ts:519

Converts mach number to equivalent airspeed (EAS) under ISA conditions.

Parameters

Parameter	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.

---

machToTas()

static machToTas(mach, soundSpeed): number

Defined in: src/sdk/math/AeroMath.ts:333

Converts mach number to true airspeed (TAS).

Parameters

Parameter	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.

---

machToTasIsa()

static machToTasIsa(mach, altitude, deltaIsa): number

Defined in: src/sdk/math/AeroMath.ts:345

Converts mach number to true airspeed (TAS), in meters per second, under ISA conditions.

Parameters

Parameter	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.

---

pressureAir()

static pressureAir(temperature, density): number

Defined in: src/sdk/math/AeroMath.ts:28

Gets the static pressure of air, in hectopascals, given temperature and density.

Parameters

Parameter	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.

---

soundSpeedAir()

static soundSpeedAir(temperature): number

Defined in: src/sdk/math/AeroMath.ts:59

Gets the speed of sound in air, in meters per second, for a given temperature.

Parameters

Parameter	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.

---

soundSpeedIsa()

static soundSpeedIsa(altitude, deltaIsa): number

Defined in: src/sdk/math/AeroMath.ts:256

Gets the speed of sound, in meters per second, at a given pressure altitude under ISA conditions.

Parameters

Parameter	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.

---

tasToCas()

static tasToCas(tas, pressure, temperature): number

Defined in: src/sdk/math/AeroMath.ts:439

Converts true airspeed (TAS) to calibrated airspeed (CAS).

Parameters

Parameter	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.

---

tasToCasIsa()

static tasToCasIsa(tas, altitude, deltaIsa): number

Defined in: src/sdk/math/AeroMath.ts:451

Converts true airspeed (TAS) to calibrated airspeed (CAS) under ISA conditions.

Parameters

Parameter	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.

---

tasToEas()

static tasToEas(tas, density): number

Defined in: src/sdk/math/AeroMath.ts:462

Converts true airspeed (TAS) to equivalent airspeed (EAS).

Parameters

Parameter	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.

---

tasToEasIsa()

static tasToEasIsa(tas, altitude, deltaIsa): number

Defined in: src/sdk/math/AeroMath.ts:474

Converts true airspeed (TAS) to equivalent airspeed (EAS) under ISA conditions.

Parameters

Parameter	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.

---

tasToMach()

static tasToMach(tas, soundSpeed): number

Defined in: src/sdk/math/AeroMath.ts:311

Converts true airspeed (TAS) to mach number.

Parameters

Parameter	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.

---

tasToMachIsa()

static tasToMachIsa(tas, altitude, deltaIsa): number

Defined in: src/sdk/math/AeroMath.ts:323

Converts true airspeed (TAS) to mach number under ISA conditions.

Parameters

Parameter	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.

---

temperatureAir()

static temperatureAir(pressure, density): number

Defined in: src/sdk/math/AeroMath.ts:48

Gets the temperature of air, in degrees Celsius, given static pressure and density.

Parameters

Parameter	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.

---

thrustCorrectionFactor()

static thrustCorrectionFactor(mach, ambientPressure): number

Defined in: src/sdk/math/AeroMath.ts:718

Calculates a thrust correction factor. Multiplying the correction factor by uncorrected thrust yields corrected thrust.

Parameters

Parameter	Type	Description
mach	number	The mach number.
ambientPressure	number	The ambient static pressure in hPa.

Returns

number

The thrust correction factor for the specified parameters.

---

totalPressureRatioAir()

static totalPressureRatioAir(mach): number

Defined in: src/sdk/math/AeroMath.ts:73

Gets the ratio of total pressure to static pressure for a given mach number in a subsonic compressible airflow.

Parameters

Parameter	Type	Description
mach	number	The mach number.

Returns

number

The ratio of total pressure to static pressure for the specific mach number.

---

totalTemperatureRatioAir()

static totalTemperatureRatioAir(mach, recovery): number

Defined in: src/sdk/math/AeroMath.ts:86

Gets the ratio of total air temperature to static air temperature for a given mach number.

Parameters

Parameter	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.