Converts calibrated airspeed (CAS) to true airspeed (TAS) using the full
compressible flow pitot-static equations (ICAO standard). CAS equals TAS only
at ISA sea level; TAS increases relative to CAS as altitude and/or temperature
deviation increases.
Valid for subsonic flight (Mach < 1.0) only. At transonic or supersonic speeds
a normal shock forms ahead of the pitot probe and a different equation set applies.
Typical commercial and general aviation operations are well within the subsonic range.
Assumes CAS equals equivalent airspeed (EAS). In practice, instrument and position
errors cause a small divergence between CAS and EAS that is aircraft-specific and
requires calibration data not available to a general-purpose library.
If oatCelsius is not provided, ISA standard temperature at the given altitude is used.
Parameters
calibratedAirspeedKt: number
Calibrated airspeed in knots.
pressureAltitudeFt: number
Pressure altitude in feet.
OptionaloatCelsius: number
Outside air temperature in degrees Celsius (optional, defaults to ISA).
Converts calibrated airspeed (CAS) to true airspeed (TAS) using the full compressible flow pitot-static equations (ICAO standard). CAS equals TAS only at ISA sea level; TAS increases relative to CAS as altitude and/or temperature deviation increases.
Valid for subsonic flight (Mach < 1.0) only. At transonic or supersonic speeds a normal shock forms ahead of the pitot probe and a different equation set applies. Typical commercial and general aviation operations are well within the subsonic range.
Assumes CAS equals equivalent airspeed (EAS). In practice, instrument and position errors cause a small divergence between CAS and EAS that is aircraft-specific and requires calibration data not available to a general-purpose library.
If oatCelsius is not provided, ISA standard temperature at the given altitude is used.