Hi, I'm very new to Fluent and Gambit and CFD but I have worked the examples in the Cornell tutorials. My question is, what type of turbulence model I should use to model the flow separation of an airfoil and how fine should the C-grid be to accurately obtain the section lift coefficient at that particular angle of attack (AOA) or higher AOA?

Previously I've used the SST k-w model with the grid being the same as the one in the Fluent tutorial by Cornell for the NACA 0012 airfoil. It has 12150 elements. The stall angle was off by about 2 degrees and the Cl obtained above it does not even approximate the experimental data. Any help in resolving this is greatly appreciated. Comments and extra readings please tell me about it. Really like to know more.

Thanks.

Generally, we decide the grid by try experiments.

Hi,

The precise stall angle prediction is still an open research topic.

Just forget to find it, especially using rough tools.

You may someday finally find it for a given airfoil with a given turbulence model, but most probably your recipe will fail for another case.

Regards

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I went any thing in separation flow over airfoil

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