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Stalling problem with simpleFoam on a NACA0012

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Old   March 2, 2010, 05:13
Default Stalling problem with simpleFoam on a NACA0012
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Damien Guénot
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Hello,

I have a problem with a simpleFoam computation : I tried to compute a 2D NACA0012 at Re=100000 (Mach~0.17) but the stalling effect on drag and lift coefficient is underestimated, as can be seen on the following curves. I am using Spalart-Allmaras model.

This mesh is the one used by Strelets (STRELETS, M., 2001, Detached eddy simulation of massively separated flows, AIAA Paper 2001-0879). It is a O shaped fine mesh (no wall function) expanding at 15 chords around the wing.
I already used this mesh with an other solver and I didn't face this problem

If someone has an idea, he would be welcome.

Thank you

Damien
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Old   March 3, 2010, 08:46
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maddalena
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Hello Damien,
welcome to the OpenFoam community!
I had similar problems some time ago. Maybe this thread can help you: Wing Aerodynamics Fluent OF 15 comparison
Good luck!

maddalena
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