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Old 9th Dec 2018, 10:46
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BEagle
 
Join Date: May 1999
Location: Quite near 'An aerodrome somewhere in England'
Posts: 25,432
Assuming ISA, +10C static air temp would be at 2525 ft pressure altitude - a TAS of 500KTAS would mean M0.763.

M0.763 at the same pressure altitude at +50C static air temp would imply ISA+40C and would require a TAS of 535KTAS.

Mach No. is the actual TAS divided by the local speed of sound.
Keeping it all simple, TAS = Mach No. x 38.97 x √ absolute static air temp

Last edited by BEagle; 9th Dec 2018 at 11:09.
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