True Airspeed - High-speed flight (for impact pressure and static pressure)
Description
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 formulasVariables
TAS | true airspeed (m/s) |
a0 | speed of sound at standard sea level (661.47 knots) (m/s) |
T | static air temperature in kelvin (k) |
T0 | temperature at standard sea level (288.15 K) (k) |
qc | impact pressure (pa) |
P | static pressure (pa) |