Naca 4412 @aoa 2
 

I am simulating a simple NACA 4412 airfoil with velocity = 2m/sec @AOA 2. This Cl value is coming quite low, around 0.38 where it should have been 0.69.
I have tried using both Spallart and K-omega turbulence model, and there is nothing wrong with the mesh and the geometry.
Can anyone figure out what the problem might be. It's really bugging me now.

Hi

I don't have much experience with Fluent.
But I suggest you to check the reference values once. Following links may be helpful.
https://www.sharcnet.ca/Software/Flu...g/node1207.htm
https://www.cfd-online.com/Forums/fl...ence-area.html
https://www.cfd-online.com/Forums/fl...es-fluent.html
Best of luck:)

I did try changing the reference area. But no luck there too. The value comes absurd.
Is it due to the low velocity?