This function calculates the planned true airspeed by correcting the planned 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 the aircraft). If the recovery factor is unknown, it can be set to 1, or ignored for Mach numbers lower than 0.3.

The function also shows the density altitude.

 

Inputs:

Pressure Altitude: 10,000 Ft

True Temperature: 2 °C

Calibrated Airspeed: 250 Kts

Recovery Factor: 0.8

 

Outputs:

True Airspeed: 288 Kts

Mach Number: 0.45

Density Altitude: 10,795 Ft