[LoGaL]

Greetings

I am currently carrying out some simulations of a naca0012 profile at different angles of attack, as preliminary stuff for my semester project. I am creating the naca profile using a matlab script and the usual naca equation, then the mesh with Salome.
I cannot manage to capture the correct lift coefficent for the airfoil: for low angles of attack i would expect it to match closely the theorical values provided by Thin Airfoil Theory, as it happens other simulations/experimental tests (Nasa measurements, Wind Tunnel test ecc)
Turns out that my simulations underestimate the lift coefficent of about 30-40% percent. Say, for example, at 6 AOA, i get about 0.4 with respect to the theorical 0.65.

Due to the small chord (about 0.3 m )of the airfoil we want to use in the wind tunnel with my professor, the simulation type that i am running is laminar.
I am attaching controlDicts, initial conditions ecc ecc (the mesh z direction is 0.03)
I initially used simpleFoam solver, but since residuals didn't get too low on Uy,P i switched to pisoFoam (lately, i've been also initializing it using a potential Flow solution)
I tried with different meshes (all structured, but with different refinements ecc) with no avail. In all cases, the trailing edge was sharp.
From what i can see visualizing the solution, seems like OpenFoam overpredicts Boundary Layer separation, as i already have large bubbles at the already mentioned 6 AOA, which i guess it shouldn't happen. This seems consistent with the underpredicted lift coefficent with respect to the correct one.

I was wondering wether one of you might spot a stupid mistake i made and/or provide tips/suggestions to solve the issue

Thank you very much!

[sangeet]

Hello.
Do you still need help?

[Artur.Ant]

Did you solve your case?

[gokulravi.pgt]

Do you still need the help to solving it?