Simulation with the profil A Airfoil
 
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.



 

Lift coefficient graph
 
 

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