[Luk_Fiz]

Hi all.
I am simulating simple 2D aerofoils (f.e. Joukovsky) with CFX 11 and compare results with JavaFoil, XFoil and others. AOA are very moderate (up to 8deg), Re~250000.
The problem is that results shows constant overestimation of Cp in the region near the leading edge. On the pressure site the Cp reaches up to 1.1, while on the suction site it is approximately -1.6 while other sources shows up to -1.8-2.
My Cp i CFX post is defined:
(pressure-TurbulencePressure)/(0.5*Denisty(inlet)*Velocity(inlet))

I have been trying everything:
- compressible/incompressible,
- mesh,
- turbulence model, conditions,
- AOA, Re
- ......

What else can it be?

Luk