This function calculates the true airspeed by correcting the calibrated airspeed for temperature and air density.

The airspeed is also shown as Mach number. For Mach numbers greater than 0.3, the calculations account for compressibility and recovery factor (depending on aircraft). If the recovery factor is unknown, it can be set to 1, or ignored for Mach numbers lower than 0.3.

 

Inputs:

Pressure Altitude: 10,000 Ft

Indicated Temperature: 2 °C

Calibrated Airspeed: 250 Kts

Recovery Factor: 0.8

 

Outputs:

True Airspeed: 288 Kts

Mach Number: 0.45