[prakashPra]

I am running simulation for 2D airfoil NACA0015 using simpleFoam. I am getting approximate half the values of Cl for various angle of attack. When I halve the value of area I get the correct result of Cl. I am confused what I am doing wrong. I am attaching condition for angle of attack 6 deg and Re10^5. Please guide me through it.
/*--------------------------------*- C++ -*----------------------------------*\
| ========= | |
| \\ / F ield | OpenFOAM: The Open Source CFD Toolbox |
| \\ / O peration | Version: 4.1 |
| \\ / A nd | Web: www.OpenFOAM.org |
| \\/ M anipulation | |
\*---------------------------------------------------------------------------*/
FoamFile
{
version 2.0;
format ascii;
class dictionary;
location "system";
object controlDict;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

application simpleFoam;

startFrom latestTime;

startTime 0;

stopAt endTime;

endTime 4500;

deltaT 1;

writeControl timeStep;

writeInterval 50;

purgeWrite 0;

writeFormat ascii;

writePrecision 6;

writeCompression off;

timeFormat general;

timePrecision 6;

runTimeModifiable true;

functions
{
forces1
{
type forceCoeffs;
libs ("libforces.so");
writeControl timeStep;
writeInterval 1;
patches ( "AIRFOIL");
rho rhoInf
log true;
rhoInf 1.225;
liftDir (-0.104 0.994 0);
dragDir (0.994 0.104 0);
CofR (0 0 0);
pitchAxis (0 0 1);
magUInf 1.48;
lRef 1;
Aref 0.5;
}


}
// ************************************************** *********************** //
/*--------------------------------*- C++ -*----------------------------------*\
| ========= | |
| \\ / F ield | OpenFOAM: The Open Source CFD Toolbox |
| \\ / O peration | Version: 5 |
| \\ / A nd | Web: www.OpenFOAM.org |
| \\/ M anipulation | |
\*---------------------------------------------------------------------------*/
FoamFile
{
version 2.0;
format ascii;
class volVectorField;
object U;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions [0 1 -1 0 0 0 0];

internalField uniform (1.47 0.155 0);

boundaryField
{
AIRFOIL
{
type noSlip;
}
INLET
{
type fixedValue;
value uniform (1.47 0.155 0);
}
OUTLET
{
type zeroGradient;
}
TOP
{
type fixedValue;
value uniform (1.47 0.155 0);
}
BOTTOM
{
type fixedValue;
value uniform (1.47 0.155 0);
}
frontAndBackPlanes
{
type empty;
}
}

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