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2D NACA0015 aerodynamic coefficients computimg

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Old   May 3, 2011, 01:25
Question 2D NACA0015 aerodynamic coefficients computimg
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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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Old   May 3, 2011, 12:58
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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 check it out!
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