Here the Navier-Stockes equations are considered. The fluid is viscous in this part.Boundary layer on the airfoil and grid

It was told in the introduction that the grid used for the profile A is very refined near the wing. On the figure above the fineness of the boundary layer and of the mesh is obvious.

Influence of the incidence

5 degres incidence

10 degres incidence

25 degres incidence

The Mach number used in this part is M0=0.30. So the flow can be assumed as incompressible.

Lift coefficient
graph