/*--------------------------------*- C++ -*----------------------------------*\
|       o          |                                                          |
|    o     o       | HELYX-OS                                                  |
|   o   O   o      | Version: v2.4.0                                           |
|    o     o       | Web:     http://www.engys.com                            |
|       o          |                                                          |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version 2.0;
    format ascii;
    class dictionary;
    location system;
    object controlDict;
}

    startFrom startTime;
    startTime 0;
    stopAt endTime;
    endTime 10.0;
    deltaT 0.001;
    writeControl adjustableRunTime;
    writeInterval 0.1;
    purgeWrite 100;
    writeFormat ascii;
    writePrecision 10;
    writeCompression uncompressed;
    timeFormat general;
    timePrecision 6;
    graphFormat raw;
    runTimeModifiable true;
    adjustTimeStep true;
    maxCo 1.0;
    maxDeltaT 0.1;

functions
{
    #include "forceCoeffs"
}
// functions
// {
//     forces
//     {
//         type            forceCoeffs;
//         libs            (forces);
//         writeControl    writeTime;
//
//         patches
//         (
//             skoda
//         );
//
//         rhoInf      1;
//
//         CofR        (0 0 0);
//         liftDir     (0 0 1);
//         dragDir     (1 0 0);
//         pitchAxis   (0 1 0);
//         magUInf     16.;
//         lRef        1;
//         Aref        1;
//     }
// }

// Coefficients
// {
// type forceCoeffs;
// libs ("libforces.so");
// log     yes;
// writeControl timeStep;
// writeInterval 0.001;
// patches (skoda);
// rho rhoInf;
// rhoInf 1025; // your fluid density
// liftDir (0 0 1); // direction of lift. In this case it is y direction
// dragDir (1 0 0);
// pitchAxis (0 1 0);
// CofR (9.75 10 0); // center of rotation.
// log true;
// magUInf 16; // inlet velocity
// lRef 1; // airfoil lenght
// Aref 1; //airfoil area
// }