When air is induced into a gas turbine inlet, the increase in velocity of the air will lead to an associated reduction in static temperatue and static pressure.(adsbygoogle = window.adsbygoogle || []).push({});

How do you calculate these, that is, reduced static temp and pressures, given only Mach number, gamma, and perhaps total pressure ?

The whole idea is to analyse whether condensation will take place or not. Kindly help.

Thanks.

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# Aerospace Calculating reduction in static temperature and pressure

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