CFD Online Discussion Forums - wrong Aerodynamic coefficient

Hello guys,

i'm doing a work on a NACA 4415 with simpleFoam solver and i have some trouble with Cd that's a lot higher than expected (0.015 vs 0.008).

here's the link of the mesh
https://picasaweb.google.com/1086153...75949717864098

i'm using bounded Gauss upwind for U, k, eps
U inlet 50
Re = 3e6

and the ControlDict

Code:

 forceCoeffs

    {

        type            forceCoeffs;

        functionObjectLibs ( "libforces.so" );

        outputControl   timeStep;

        outputInterval  1;



        patches

        (

            profile

        );



        pName       p;

        UName       U;

    rhoName        rhoInf;

        log         true;

        rhoInf      1.16;

        CofR        ( 0 0 0 );

        liftDir     ( 0 1 0 );

        dragDir     ( 1 0 0 );

        pitchAxis   ( 0 0 1 );

        magUInf     50;

    lRef    1;        

    Aref    1;

    //lRef        0.55;

        //Aref        0.0825;

    }

someone could help me to solve this problem?
Thank you all,

Marcello