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Total Pressure Calculation

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Old   July 7, 2020, 19:37
Default Total Pressure Calculation
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Dear all!

I would like to simulate air flow around a rotating blade with rpm=17188.7, Compressible, transonic flow, and just one blade with cyclic conditions by using OpenFOAM extend 4.0.

Which mach number do we use for to calculate -inlet or outlet- total pressure? ( relative mach? or absolute mach? )
Pt=P( 1 + (gamma-1)*0.5*mach(?)^2 )^(gamma/(gamma-1))

Thanks for your help.
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Old   July 8, 2020, 05:46
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Santiago Lopez Castano
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You kind of answering your own question there
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