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NASA stage 67 efficiency issue

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Old   April 26, 2023, 04:30
Default NASA stage 67 efficiency issue
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Im currently having trouble with the steady simulation of the transonic compressor NASA rotor 67 ( full stage) in fluent. I have run the case in CFX and found a great match with the experimental data. However, when i try to run it with fluent with the same conditions the results are different, and the isentropic efficiency is higher as well as the velocity contours. The pressure ratio remains the same. I don't understand why does anybody have a clue or some advice? I can send you my results if you need.

My conditions are the following:
Turbulence: k-epsilon scalable wall function,
Inlet: P= 101325 Pa and T= 288.15 K normal to boundary
Outlet: Ps= 137 000 Pa as an average pressure.
Interface : mixing plane

I also initialized the axial velocity to get rid of the reverse flow by putting the axial velocity at the inlet:
X velocity = 164 m/s.

Thanks for your help !
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axial compressor, fluent, turbo-machinery

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