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? )
Formula:
Pt=P( 1 + (gamma-1)*0.5*mach(?)^2 )^(gamma/(gamma-1))

Thanks for your help.

You kind of answering your own question there