2D NACA0015 aerodynamic coefficients computimg
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!
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