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hi everyone,
I'm focusing on solving an AIRFOIL NACA 0006 in 2D, I have to find the correct Coefficient of DRUG and LIFT, but after several times I haven't get the clue yet.

I've got a section angle of attack about -4 degrees, which means according to the tables a value for Cl=-0.4,-0.5 and Cd=0.010,0.014 i suppose?! (CORRECT ME IF IS WRONG, PLEASE)



I'm using this function objects for the calculation of the Coeffs::

functions
{ forces
{ type forceCoeffs;
functionObjectLibs ("libforces.so");
outputControl timeStep;
outputInterval 1;
patches (profiloalare);
pName p;
UName U;
rhoName rhoInf;
log true;
rhoInf 1.2;
liftDir (0.069756474 0.99756405 0);
dragDir (0.99756405 -0.069756474 0);
//liftDir (0 1 0);
//dragDir (1 0 0);
CofR (1.0375 0 0);
pitchAxis (0 0 -1);
magUInf 21.6867;
lRef 4.15;
Aref 4.15;
} }

I think I'm using a good mesh, (i used youtube videos to create the best mesh possible)



I settled all the named section, wall for the airfoil, inlet and outlet for the edges.

I had post as system settings:

divSchemes
{
default none;
div(phi,U) bounded Gauss linearUpwind grad(U);
div(phi,nuTilda) bounded Gauss linearUpwind grad(nuTilda);
div((nuEff*dev2(T(grad(U))))) Gauss linear;
}

relaxationFactors
{
fields
{
p 0.3;

}
equations
{
U 0.7;
nuTilda 0.7;
}
}

simulationType RAS;

RAS
{
RASModel SpalartAllmaras;

turbulence on;

printCoeffs on;
}

transportModel Newtonian;

rho [1 -3 0 0 0 0 0] 1.2;

nu [0 2 -1 0 0 0 0] 1.5e-05;


I launch the simpleFoam, but in the end my coefficient are SO WRONG! and i don't know why!

I said the should be Cl=-0.4,-0.5 and Cd=0.010,0.014, but mine values are about Cl=-0.83 and Cd=0.027.

Anyone has any suggestion, please??