Getting a non zero lift coefficient for a simetric arifoil at 0 degrees AOA
 

Hello, everybody.

I've been trying to model a 2D (obviously) airfoil in Ansys. Since this was my first time with this software, I followed a YouTube video (https://www.youtube.com/watch?v=nzvE...annel=AnthonyT) of a guy that does the same thing only with another airfoil (non symmetric one). The thing is that I do exactly everything the guy does, but yet the results are wrong. I get a 2.36e-3 lift coefficient (about 2.7 N of lift force) when I should be getting at least something smaller (e-6, for example).

I have checked the geometry, mesh and setup multiple times. I even started from scratch several times, yet I get the same results time and time again.

My mesh is totally symmetric (image attached) and the y_plus requirements are met (I get a 0.5 max y_plus, check the results image attached). I am using the k-omega model for turbulence. My velocity is 43.8m/s at 0 AOA, fluid is air, obviously (rho=1.225 kg/m^3 and mu=1.7894e-05 Pa s).

I have also tried other AOA and the results are wrong too, and it is not close (I compare my CFD results with experimental data).

What can I do?

Thanks in advance!

P.S I hope I have provided enough info. If not, lmk.