2D NACA0015 aerodynamic coefficients computimg
 

Hi,

I'm fresh in Fluent. I have an easy question here.

I want to get the aerodynamic coefficients of NACA0015 airfoil. But the results do not match with the data of others.
So I need some help about the set in Fluent, such as choose Laminar or Spalart-Allmaras？steady or unsteady?

Thanks in advance!