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!

Hello,

normally, I'd say this is a steady case. You have to decide whether this is laminar or turbulent by calculating the Re-number...

Also be sure that your calculation area (especially behind the airfoil) is long enough and the wall y+ is acceptable. Furthermore, cell refinement at the gradients (of pressure e.g.) should be set up.

There's a tutorial at https://confluence.cornell.edu/displ...+Specification check it out!