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