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lift on airfoil NACA 2412

Posted 2016年10月10日 GMT-4 08:38 0 Replies

Abraham Mansouri
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Hi all

I'm simulating lift/drag coefficient on airfoil NACA 2412 and the value I get is underestimated, the reference value at zero angle of attack is 0.24 and I get around 0.055, I checked the mesh and Im using k-epsilon model, the drag coefficient is around 0.007 and my value is 0.01, can you pls look at my model and tell me what's wrong ?

Thank you
Abraham

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0 Replies Last Post 2016年10月10日 GMT-4 08:38
COMSOL Moderator

Hello Abraham Mansouri

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