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Cl-alpha, 3d airfoil problem.

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Old   February 14, 2011, 19:55
Default Cl-alpha, 3d airfoil problem.
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Levon
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I am trying to determine dCl/d(alpha) for a 3d airfoil however Cl is barely changing (0.38-0.42) as I vary alpha (0-10 degrees), any help?

I only need preliminary results so my mesh is fairly coarse.

Thanks.
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Old   February 15, 2011, 03:07
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If you are reporting Cl from the monitors, are you sure your reference values are correct?

If that's not it, I'd try refining your mesh first.
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Old   February 15, 2011, 10:29
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My reference values are good, Fluent is simply underestimating the force produced by the airfoil as it changes angles. I also forgot to mention that my first mesh refinement did not fix the problem.

I am very closely following the 2D wing tutorials, at this point my wing is just a 2D airfoil that has been extruded.
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