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Wrong result of NACA0012 for 10 angle of attack

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Old   June 27, 2016, 05:56
Default Wrong result of NACA0012 for 10 angle of attack
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Hi ,everyone,
I am newer for CFD,doing the simulation of NACA0012 for 10 deg angle of attack. But I always do not get correct result. All the procedure are followed by the Youtube. The following are the parameters of setting.
1 Density: 1.225kg/s
2 Viscosity Coefficient : 1.8375E-05 kg/(m*s)
3 Character Length: 1.0m
4 Velocity: 90m/s
5 Reynold number: 6.0E+06
6 Y+: 1.0
7 Wall adjacent distance: 4e-3mm
8 Total grid number: 180,000
9 Spalart-Allmaras model and K-Omega-SST turbulent model
10 Boundary conditions: Velocity inlet/Outflow/Symmetry/Wall

I must use velocity inlet boundary in order to add some velocity fluctuation on it. So I can not use the compressible solver. The iteration step has been reached up to 145000, but the flow field also is divergence and the result is not unstable. I am afraid that I have set the fault parameters or conditions.
Attached file is my case and Cp and Cf distributions along the lower wall. The result is wrong clearly. If you are available, please help me check it. Thanks very much.
My email is

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Old   August 13, 2016, 04:45
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