Wing stall prediction.
 

Hi friends!

I am having problems with the results obtained when having a higher value of angle of attack. For a NACA 0012, when I increase until 20 degrees or more, the value of cl does not drop too much,i t remains near 1. I have tried with other airfoils and the values of lift coefficients don't go down.

Is fluent capable of predicting a stall when the angle of attack is too high?
What models do you use?

(I am trying with a 2d airfoil)

Thanks!

This problem is better to be solved unsteady. Also, be sure that the mesh behind the airfoil (after separation point) is refined. Years ago at school, I remember a colleague solved this problem with fluent using Reynolds stress model and his results made sense.