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Airfoil simulation wrong pressure field at some angles of attack

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Old   December 14, 2016, 12:53
Default Airfoil simulation wrong pressure field at some angles of attack
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Lorenzo Donisi
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Hi everybody,

I am trying to simulate the flow field around a NACA 0012, using OpenFOAM (simpleFoam), at Re=6e6. I am using the SST k-omega model, with an average y+ around 30, using wall functions. The lift and drag coefficient I get are quite good if compared with xFoil and other sources.
The strange problem I am experiencing is a wrong pressure field for some angles of attack, namely 4deg and 7deg. I really cannot wonder why this is happening, or maybe the pressure fields are correct; I hope you can give me an answer in any case.

PS: is there a better utility than wallPressure to output the pressure or maybe the pressure coefficient over the airfoil?
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Old   December 14, 2016, 12:55
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Lorenzo Donisi
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These are the speed fields, I could not load all the images in the same post
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