[Turbomachine]

Dear All,

I need to plot the isentropic Mach number distribution on a compressor blade. I defined an expression using the formula:

http://www.cfd-online.com/Wiki/Isentropic_Mach_number

I am using total temperature in relative frame and static pressure so the formula in cfx post looks like this:

sqrt(((Total Pressure in Rel Frame/Pressure)^(0.4/1.4)-1)*2/0.4)

Even though the plots show high pressure gradients where the shock wave is, the Mach number in front of it is subsonic, which is meaningless.

The problem must be with how the isentropic mach number is defined and used in this case. Can someone help me out with this??

Thank you very much