Airfoil Convergence Problem at High Angle of Attack
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Hi
I'm simulating an airfoil in range of 0-18 (deg) angle of attack, And I have convergence problem at 16...18 degree. flow is incompressible, Geometry is fixed and flow has direction, K-Omega SST turbulent model at default settings, Reference values are set (Area = chord length), Standard initialization from inlet, https://www.cfd-online.com/Forums/at...1&d=1658323334 https://www.cfd-online.com/Forums/at...1&d=1658323355 https://www.cfd-online.com/Forums/at...1&d=1658323387 |
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To some extent done
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It was a meshing problem and I tried to refine the mesh and finally, It was Solved, It was a steady state modeling, Therefore, I was unable to use a pseudo time step, I did it with FMG initialization, But it took much time and iterations. All the best Arash |
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