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Old   October 11, 2013, 11:10
Default Thin airfoil subsonic Stall
Join Date: May 2013
Location: South Africa
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I am analysing a supercritical airfoil at subsonic (Mach 0.2) conditions. I am struggling with determining the correct stall angle. Stall should occur at around 8.5 degrees with a sharp leading edge stall but my model shows a gradual trailing edge stall.

I have tried various turbulence models as well as considerable grid refinements but nothing seems to work.

Does anyone have any ideas/hints/tips?
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low mach, stall, supercritical, thin airfoil

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