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!
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!
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