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wrong Aerodynamic coefficient

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Old   January 26, 2016, 08:48
Default wrong Aerodynamic coefficient
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Marcello
Join Date: Jul 2015
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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
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