Crabwise · Library
Altitude & airspeed · True airspeed
Pressure and density altitude, TAS, Mach
Pressure and density altitude, TAS, Mach
Educational calculation only. Check current aircraft limits, weather, performance and reserve requirements using approved information.
Results
Example calculation
True airspeed: worked out from the values already filled in the form above.
Inputs
- Calibrated airspeed (kt): 150
- Pressure altitude (ft): 5,000
- Outside air temperature (°C): 5
Result
- True airspeed: 161.35927
- Mach number: 0.248283523
- Speed of sound (kt): 649.899229
Related tools
Use calibrated airspeed as the input
Enter CAS, pressure altitude and outside air temperature. The native compressible-air calculation derives true airspeed, Mach number and speed of sound for its supported subsonic atmosphere range.
Indicated airspeed is not automatically calibrated airspeed. Apply the aircraft’s airspeed calibration information before treating IAS as CAS. This worksheet does not apply a specific aircraft’s position or instrument corrections.
Keep the atmosphere inputs together
Pressure altitude and temperature must describe the same condition as the speed input. Results outside the supported model are rejected. Ground speed also depends on wind and is a separate quantity.