This function calculates the calibrated airspeed corresponding to a required true airspeed by applying corrections for temperature and pressure altitude.

 

Inputs:

Pressure Altitude: 7,500 Ft

True Temperature: 10° C

True Airspeed: 90 Kts

 

Outputs:

Calibrated Airspeed: 79 Kts

Density Altitude: 8,644 Ft