True Airspeed - High-speed flight (for impact pressure and static pressure)


TAS can be calculated as a function of Mach number and static air temperature. Combining the TAS for High-speed flight with the expression for Mach number gives an expression for TAS as a function of impact pressure, static pressure and static air temperature (valid for subsonic flow).

Related formulas


TAStrue airspeed (m/s)
a0speed of sound at standard sea level (661.47 knots) (m/s)
Tstatic air temperature in kelvin (k)
T0temperature at standard sea level (288.15 K) (k)
qcimpact pressure (pa)
Pstatic pressure (pa)