Cl-alpha, 3d airfoil problem.
 

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.

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.

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.