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 | - |
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.