Subsonic and Transonic Flow
 

Hello there,

I am simulating a 4-stage axial compressor with subsonic flow.
When I evaluated the mach-number at the inlet of the first rotor row, the Mach-number near the Shroud reached 0.85.
For me this is a little but curious since I defined the flow with subsonic.
Is it normal, that the Flow exceeds 0.8 for transonic flow conditions?

Thank you very much!

yes very much normal

Thanks for the answer :)

But is there any explanation for this ?

isnt is the velocity triangle. at tip the blade speed is higher, so the mach number

you have to check it is relative mach number or mach number.

I only can choose Mach Number and Mach Number in Stn Frame.
And for the Rotor I've chosen the regular Mach Number.

it is relative mach number