[appa]

Hello everybody,
I am trying ti simulate an airfoil using the solver simpleFoam. I want to have a pressure distribution as if the flux is real. The airfoil I'm using is a NASA/Langley GAW-1, it's used on the piper Tomahawk, the velocity is the cruise velocity =45m/s , and the ambiant pressure should be 797.952hPa at an altitude of 2000m. The file p at the 0 directory is modified in this way

dimensions [0 2 -2 0 0 0 0];

internalField uniform 79795.2;

boundaryField
{
inlet
{

type fixedValue ;
value uniform 79495.2


}

outlet
{
type fixedValue ;
value uniform 79495.2
}

wall
{
type zeroGradient;
}

frontAndBack
{
type empty;
}
}

but when I simulate the case I get positif pressure over the upper surface of the airfoil which is impossible!!can someone help me please ?
can