Issue with CL and CD Values When Changing Airfoil Polar in FLOWUnsteady

[prem-tekkr]

Hello,

I ran the wing example and tried changing the airfoil polar to different airfoils, such as NACA and GOE airfoils with same parameters. However, I’m getting the same CL values for all the airfoils, with only a slight change in CD values as shown below.

Cl vs Alpha for 3 different airfoils.

Could anyone explain why this is happening? Any help would be greatly appreciated!

Thanks in advance.