Hello everyone, I need some help regarding an incompressible simulation around an airfoil (angle of attack = 10°, Reynolds number = 15e6). The simulation converges nicely, as far as I can tell. The lift coefficient is physically plausible and the results are similar to the experiment. When I plot the velocity field, it also looks as expected. However, when I plot divergence and vorticity, I'm seeing results that I did not expect. Ill post the plots here: