[antonio_ing]

Hi everybody

i'm trying to calculate the lift coefficient around a NACA0015 airfoil with the spalart-allmaras model. I have created the mesh with gmsh using two surfaces (profile1 and profile2) for the higher and lower profile surface. I have found some post where someone descrived how to calculate the force coefficients. But, if i take the profile at 3 degrees of attack the lift coefficient should be 0.5 (from xfoil) but it is 0.02 from OpenFoam.
The chord is 0.1m, the freestream velocity 10m/s and the Re=1e5. This is the controlDict file:

/*--------------------------------*- C++ -*----------------------------------*\
| ========= | |
| \ / F ield | OpenFOAM: The Open Source CFD Toolbox |
| \ / O peration | Version: 1.5 |
| \ / A nd | Web: http://www.OpenFOAM.org |
| \/ M anipulation | |
\*---------------------------------------------------------------------------*/
FoamFile
{
version 2.0;
format ascii;
class dictionary;
object controlDict;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

application simpleFoam;

startFrom startTime;

startTime 3000;

stopAt endTime;

endTime 3010;

deltaT 1;

writeControl timeStep;

writeInterval 5;

purgeWrite 0;

writeFormat ascii;

writePrecision 6;

writeCompression uncompressed;

timeFormat general;

timePrecision 6;

runTimeModifiable yes;

functions
(
forces
{
type forces;
functionObjectLibs ("libforces.so"); //Lib to load -> dylib on Mac and so on Linux
patches (profile1 profile2);//Name of patche to integrate forces
rhoInf 1.0; //Reference density for fluid - can be changed later ...
CofR ( 0 0 0);
}
forceCoeffs
{
type forceCoeffs;
functionObjectLibs ("libforces.so");
patches (profile1 profile2);
rhoInf 1.0;
CofR (0 0 0);
liftDir (0 1 0);
dragDir (1 0 0);
pitchAxis (0 0 0);
magUInf 10.0;
lRef 0.1;
Aref 0.1;
} );

// ************************************************** *********************** //

any suggestions?

thanks in advance