[hntter]

Hello everyone, I'm doing my postgraduate project and one part of it is to validate the naca0012 lift and drag coefficient. The flow domain and mesh was based on the cornell toturial but I just can't get the similar results compared to experimental data.

My chord length is 1 m. Pressured based solver. S-A model. and Re number is 3*10e6 (velocity=44m/s) with 1.225 density and 1.8e-5 viscosity. The values of lift coefficient and drag coefficient is always smaller than experimental, for example: in 8 degree, my results is Cl=0.8, but experimental Cl=nearly 1.1..The difference is too big.

Can anybody give me some advice about how to solve these? thanks.

I have another question..Why the shape of flow domain in airfoil analysis is always C-mesh?