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mekim July 7, 2020 18:37

Total Pressure Calculation
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.

Santiago July 8, 2020 04:46

You kind of answering your own question there

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