[Fasouras]

Hi



I am conducting a 2d airfoil analysis on a naca0015. i am using standard k-e model, water as material and i am doing it for a number of angle of attacks (0,2,4,6,8). I am changing the angle of attack as phrased below:
in boundary conditions --> inlet--> i choose components an the where x--> vcos(aoa) and where y--> vsin(aoa) (where v equals the speed,10.29 m/s)



also in monitor cd and cl:


cd: x-->cos(aoa) cl: x--> -sin(aoa)

y-->sin(aoa) y--> cos(aoa)


and i proceed like this changing aoas and changing models of turbulence.
The cl and cd seem legit from the results, but when i open cfd post, while the velocity seems legit and higher on the upper surface as supposed, the pressure seems wrongly higher again on the upper surface.



Does any of you guys has any theory, or a link to a post i might have missed?


Thanks in advance!



(btw this research is being done to decide the right airfoil to be attached to a sailing hydrofoil)