OpenFOAM v2512 high-angle steady screening. All cases missed full convergence. Internal field arrays omitted from boundary settings excerpts.

Case angle 0 degrees / system/controlDict
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //
FoamFile
{
    version         2;
    format          ascii;
    class           dictionary;
    object          controlDict;
}

application     simpleFoam;

startFrom       latestTime;

startTime       0;

stopAt          endTime;

endTime         1000;

deltaT          1;

writeControl    timeStep;

writeInterval   200;

purgeWrite      2;

writeFormat     binary;

writePrecision  8;

writeCompression off;

timeFormat      general;

timePrecision   6;

runTimeModifiable true;

functions
{
    force_airframe
    {
        type            forces;
        libs            ( forces );
        patches         ( "aircraft.*" );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_fuselage
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_fuselage );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_wing
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_wing );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_tail
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_tail );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_booms
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_booms );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_nacelles
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_nacelles );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_gear
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_gear );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    coefficients
    {
        type            forceCoeffs;
        libs            ( forces );
        patches         ( "aircraft.*" );
        rho             rhoInf;
        rhoInf          1.225;
        liftDir         ( 0 0 1 );
        dragDir         ( 1 0 0 );
        pitchAxis       ( 0 1 0 );
        CofR            ( -1.5 0 2.3 );
        magUInf         44.704;
        lRef            1.55949;
        Aref            11.4079;
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    flux_inlet
    {
        type            surfaceFieldValue;
        libs            ( fieldFunctionObjects );
        regionType      patch;
        name            inlet;
        operation       sum;
        fields          ( phi );
        writeFields     false;
        log             false;
        writeControl    timeStep;
        writeInterval   20;
    }
    flux_outlet
    {
        type            surfaceFieldValue;
        libs            ( fieldFunctionObjects );
        regionType      patch;
        name            outlet;
        operation       sum;
        fields          ( phi );
        writeFields     false;
        log             false;
        writeControl    timeStep;
        writeInterval   20;
    }
    flux_farfield
    {
        type            surfaceFieldValue;
        libs            ( fieldFunctionObjects );
        regionType      patch;
        name            farfield;
        operation       sum;
        fields          ( phi );
        writeFields     false;
        log             false;
        writeControl    timeStep;
        writeInterval   20;
    }
    yPlus
    {
        type            yPlus;
        libs            ( fieldFunctionObjects );
        executeControl  writeTime;
        writeControl    writeTime;
        log             true;
    }
    wallShearStress
    {
        type            wallShearStress;
        libs            ( fieldFunctionObjects );
        patches         ( "aircraft.*" );
        executeControl  writeTime;
        writeControl    writeTime;
    }
    residuals
    {
        type            solverInfo;
        libs            ( utilityFunctionObjects );
        fields          ( p U k omega );
        writeControl    timeStep;
        writeInterval   1;
        log             false;
    }
}


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


Case angle 0 degrees / system/fvSchemes
FoamFile { version 2.0; format ascii; class dictionary; object fvSchemes; }

ddtSchemes {default steadyState;}
gradSchemes {default Gauss linear; grad(U) cellLimited Gauss linear 1;}
divSchemes {default none; div(phi,U) bounded Gauss limitedLinearV 1; div(phi,k) bounded Gauss upwind; div(phi,omega) bounded Gauss upwind; div((nuEff*dev2(T(grad(U))))) Gauss linear;}
laplacianSchemes {default Gauss linear limited 0.5;}
interpolationSchemes {default linear;}
snGradSchemes {default limited 0.5;}
wallDist {method meshWave;}


Case angle 0 degrees / system/fvSolution
FoamFile { version 2.0; format ascii; class dictionary; object fvSolution; }

solvers {
 p {solver GAMG; smoother GaussSeidel; tolerance 1e-8; relTol 0.001;}
 Phi {$p;}
 U {solver smoothSolver; smoother symGaussSeidel; tolerance 1e-8; relTol 0.01;}
 "(k|omega)" {solver smoothSolver; smoother symGaussSeidel; tolerance 1e-8; relTol 0.01;}
}
SIMPLE {nNonOrthogonalCorrectors 1; consistent no; pRefCell 0; pRefValue 0;}
potentialFlow {nNonOrthogonalCorrectors 6;}
relaxationFactors {fields {p 0.25;} equations {U 0.5; k 0.5; omega 0.5;}}
cache {grad(U);}


Case angle 0 degrees / system/decomposeParDict
FoamFile {version 2; format ascii; class dictionary; object decomposeParDict;}
numberOfSubdomains 4; method scotch;


Case angle 0 degrees / 0/U
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volVectorField;
    location    "0";
    object      U;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

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

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            fixedValue;
        value           uniform (44.704 0 0);
    }
    outlet
    {
        type            inletOutlet;
        inletValue      uniform (44.704 0 0);
        value           uniform (44.704 0 0);
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            freestreamVelocity;
        freestreamValue uniform (44.704 0 0);
        value           uniform (44.704 0 0);
    }
    aircraft_fuselage
    {
        type            noSlip;
    }
    aircraft_wing
    {
        type            noSlip;
    }
    aircraft_tail
    {
        type            noSlip;
    }
    aircraft_booms
    {
        type            noSlip;
    }
    aircraft_nacelles
    {
        type            noSlip;
    }
    aircraft_gear
    {
        type            noSlip;
    }
}


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


Case angle 0 degrees / 0/p
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volScalarField;
    location    "0";
    object      p;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions      [0 2 -2 0 0 0 0];

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            zeroGradient;
    }
    outlet
    {
        type            fixedValue;
        value           uniform 0;
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            freestreamPressure;
        freestreamValue uniform 0;
        value           uniform 0;
    }
    aircraft_fuselage
    {
        type            zeroGradient;
    }
    aircraft_wing
    {
        type            zeroGradient;
    }
    aircraft_tail
    {
        type            zeroGradient;
    }
    aircraft_booms
    {
        type            zeroGradient;
    }
    aircraft_nacelles
    {
        type            zeroGradient;
    }
    aircraft_gear
    {
        type            zeroGradient;
    }
}


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


Case angle 0 degrees / 0/k
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volScalarField;
    location    "0";
    object      k;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions      [0 2 -2 0 0 0 0];

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            fixedValue;
        value           uniform 0.29976714;
    }
    outlet
    {
        type            inletOutlet;
        inletValue      uniform 0.29976714;
        value           uniform 0.29976714;
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            inletOutlet;
        inletValue      uniform 0.29976714;
        value           uniform 0.29976714;
    }
    aircraft_fuselage
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_wing
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_tail
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_booms
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_nacelles
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_gear
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
}


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


Case angle 0 degrees / 0/omega
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volScalarField;
    location    "0";
    object      omega;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

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

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            fixedValue;
        value           uniform 9.9961183;
    }
    outlet
    {
        type            inletOutlet;
        inletValue      uniform 9.9961183;
        value           uniform 9.9961183;
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            inletOutlet;
        inletValue      uniform 9.9961183;
        value           uniform 9.9961183;
    }
    aircraft_fuselage
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_wing
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_tail
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_booms
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_nacelles
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_gear
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
}


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


Case angle 0 degrees / 0/nut
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volScalarField;
    location    "0";
    object      nut;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions      [0 2 -1 0 0 0 0];

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            calculated;
        value           uniform 0.029988355;
    }
    outlet
    {
        type            calculated;
        value           uniform 0.029988355;
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            calculated;
        value           uniform 0.029988355;
    }
    aircraft_fuselage
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_wing
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_tail
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_booms
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_nacelles
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_gear
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
}


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


Case angle 0 degrees / constant/turbulenceProperties
FoamFile { version 2.0; format ascii; class dictionary; object turbulenceProperties; }
simulationType RAS; RAS {RASModel kOmegaSST; turbulence on; printCoeffs on;}

Case angle 0 degrees / constant/transportProperties
FoamFile { version 2.0; format ascii; class dictionary; object transportProperties; }
transportModel Newtonian; nu 1.46e-05;


Case angle 20 degrees / system/controlDict
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //
FoamFile
{
    version         2;
    format          ascii;
    class           dictionary;
    object          controlDict;
}

application     simpleFoam;

startFrom       latestTime;

startTime       0;

stopAt          endTime;

endTime         1000;

deltaT          1;

writeControl    timeStep;

writeInterval   200;

purgeWrite      2;

writeFormat     binary;

writePrecision  8;

writeCompression off;

timeFormat      general;

timePrecision   6;

runTimeModifiable true;

functions
{
    force_airframe
    {
        type            forces;
        libs            ( forces );
        patches         ( "aircraft.*" );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_fuselage
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_fuselage );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_wing
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_wing );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_tail
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_tail );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_booms
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_booms );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_nacelles
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_nacelles );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    force_gear
    {
        type            forces;
        libs            ( forces );
        patches         ( aircraft_gear );
        rho             rhoInf;
        rhoInf          1.225;
        CofR            ( -1.5 0 2.3 );
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    coefficients
    {
        type            forceCoeffs;
        libs            ( forces );
        patches         ( "aircraft.*" );
        rho             rhoInf;
        rhoInf          1.225;
        liftDir         ( -0.34202 0 0.939693 );
        dragDir         ( 0.939693 0 0.34202 );
        pitchAxis       ( 0 1 0 );
        CofR            ( -1.5 0 2.3 );
        magUInf         44.704;
        lRef            1.55949;
        Aref            11.4079;
        log             false;
        writeControl    timeStep;
        writeInterval   1;
    }
    flux_inlet
    {
        type            surfaceFieldValue;
        libs            ( fieldFunctionObjects );
        regionType      patch;
        name            inlet;
        operation       sum;
        fields          ( phi );
        writeFields     false;
        log             false;
        writeControl    timeStep;
        writeInterval   20;
    }
    flux_outlet
    {
        type            surfaceFieldValue;
        libs            ( fieldFunctionObjects );
        regionType      patch;
        name            outlet;
        operation       sum;
        fields          ( phi );
        writeFields     false;
        log             false;
        writeControl    timeStep;
        writeInterval   20;
    }
    flux_farfield
    {
        type            surfaceFieldValue;
        libs            ( fieldFunctionObjects );
        regionType      patch;
        name            farfield;
        operation       sum;
        fields          ( phi );
        writeFields     false;
        log             false;
        writeControl    timeStep;
        writeInterval   20;
    }
    yPlus
    {
        type            yPlus;
        libs            ( fieldFunctionObjects );
        executeControl  writeTime;
        writeControl    writeTime;
        log             true;
    }
    wallShearStress
    {
        type            wallShearStress;
        libs            ( fieldFunctionObjects );
        patches         ( "aircraft.*" );
        executeControl  writeTime;
        writeControl    writeTime;
    }
    residuals
    {
        type            solverInfo;
        libs            ( utilityFunctionObjects );
        fields          ( p U k omega );
        writeControl    timeStep;
        writeInterval   1;
        log             false;
    }
}


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


Case angle 20 degrees / system/fvSchemes
FoamFile { version 2.0; format ascii; class dictionary; object fvSchemes; }

ddtSchemes {default steadyState;}
gradSchemes {default Gauss linear; grad(U) cellLimited Gauss linear 1;}
divSchemes {default none; div(phi,U) bounded Gauss limitedLinearV 1; div(phi,k) bounded Gauss upwind; div(phi,omega) bounded Gauss upwind; div((nuEff*dev2(T(grad(U))))) Gauss linear;}
laplacianSchemes {default Gauss linear limited 0.5;}
interpolationSchemes {default linear;}
snGradSchemes {default limited 0.5;}
wallDist {method meshWave;}


Case angle 20 degrees / system/fvSolution
FoamFile { version 2.0; format ascii; class dictionary; object fvSolution; }

solvers {
 p {solver GAMG; smoother GaussSeidel; tolerance 1e-8; relTol 0.001;}
 Phi {$p;}
 U {solver smoothSolver; smoother symGaussSeidel; tolerance 1e-8; relTol 0.01;}
 "(k|omega)" {solver smoothSolver; smoother symGaussSeidel; tolerance 1e-8; relTol 0.01;}
}
SIMPLE {nNonOrthogonalCorrectors 1; consistent no; pRefCell 0; pRefValue 0;}
potentialFlow {nNonOrthogonalCorrectors 6;}
relaxationFactors {fields {p 0.25;} equations {U 0.5; k 0.5; omega 0.5;}}
cache {grad(U);}


Case angle 20 degrees / system/decomposeParDict
FoamFile {version 2; format ascii; class dictionary; object decomposeParDict;}
numberOfSubdomains 4; method scotch;


Case angle 20 degrees / 0/U
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volVectorField;
    location    "0";
    object      U;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

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

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            fixedValue;
        value           uniform (42.0080189196 0 15.2896684872);
    }
    outlet
    {
        type            inletOutlet;
        inletValue      uniform (42.0080189196 0 15.2896684872);
        value           uniform (42.0080189196 0 15.2896684872);
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            freestreamVelocity;
        freestreamValue uniform (42.0080189196 0 15.2896684872);
        value           uniform (42.0080189196 0 15.2896684872);
    }
    aircraft_fuselage
    {
        type            noSlip;
    }
    aircraft_wing
    {
        type            noSlip;
    }
    aircraft_tail
    {
        type            noSlip;
    }
    aircraft_booms
    {
        type            noSlip;
    }
    aircraft_nacelles
    {
        type            noSlip;
    }
    aircraft_gear
    {
        type            noSlip;
    }
}


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


Case angle 20 degrees / 0/p
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volScalarField;
    location    "0";
    object      p;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions      [0 2 -2 0 0 0 0];

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            zeroGradient;
    }
    outlet
    {
        type            fixedValue;
        value           uniform 0;
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            freestreamPressure;
        freestreamValue uniform 0;
        value           uniform 0;
    }
    aircraft_fuselage
    {
        type            zeroGradient;
    }
    aircraft_wing
    {
        type            zeroGradient;
    }
    aircraft_tail
    {
        type            zeroGradient;
    }
    aircraft_booms
    {
        type            zeroGradient;
    }
    aircraft_nacelles
    {
        type            zeroGradient;
    }
    aircraft_gear
    {
        type            zeroGradient;
    }
}


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


Case angle 20 degrees / 0/k
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volScalarField;
    location    "0";
    object      k;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions      [0 2 -2 0 0 0 0];

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            fixedValue;
        value           uniform 0.29976714;
    }
    outlet
    {
        type            inletOutlet;
        inletValue      uniform 0.29976714;
        value           uniform 0.29976714;
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            inletOutlet;
        inletValue      uniform 0.29976714;
        value           uniform 0.29976714;
    }
    aircraft_fuselage
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_wing
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_tail
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_booms
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_nacelles
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
    aircraft_gear
    {
        type            kqRWallFunction;
        value           uniform 0.29976714;
    }
}


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


Case angle 20 degrees / 0/omega
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volScalarField;
    location    "0";
    object      omega;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

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

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            fixedValue;
        value           uniform 9.9961183;
    }
    outlet
    {
        type            inletOutlet;
        inletValue      uniform 9.9961183;
        value           uniform 9.9961183;
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            inletOutlet;
        inletValue      uniform 9.9961183;
        value           uniform 9.9961183;
    }
    aircraft_fuselage
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_wing
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_tail
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_booms
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_nacelles
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
    aircraft_gear
    {
        type            omegaWallFunction;
        value           uniform 9.9961183;
    }
}


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


Case angle 20 degrees / 0/nut
/*--------------------------------*- C++ -*----------------------------------*\
| =========                 |                                                 |
| \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox           |
|  \\    /   O peration     | Version:  2512                                  |
|   \\  /    A nd           | Website:  www.openfoam.com                      |
|    \\/     M anipulation  |                                                 |
\*---------------------------------------------------------------------------*/
FoamFile
{
    version     2.0;
    format      binary;
    arch        "LSB;label=32;scalar=64";
    class       volScalarField;
    location    "0";
    object      nut;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

dimensions      [0 2 -1 0 0 0 0];

// Internal field array omitted; boundary settings follow.
boundaryField
{
    inlet
    {
        type            calculated;
        value           uniform 0.029988355;
    }
    outlet
    {
        type            calculated;
        value           uniform 0.029988355;
    }
    symmetry
    {
        type            symmetryPlane;
    }
    farfield
    {
        type            calculated;
        value           uniform 0.029988355;
    }
    aircraft_fuselage
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_wing
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_tail
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_booms
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_nacelles
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
    aircraft_gear
    {
        type            nutkWallFunction;
        value           uniform 0.029988355;
    }
}


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


Case angle 20 degrees / constant/turbulenceProperties
FoamFile { version 2.0; format ascii; class dictionary; object turbulenceProperties; }
simulationType RAS; RAS {RASModel kOmegaSST; turbulence on; printCoeffs on;}

Case angle 20 degrees / constant/transportProperties
FoamFile { version 2.0; format ascii; class dictionary; object transportProperties; }
transportModel Newtonian; nu 1.46e-05;


Common mesh / system/blockMeshDict
FoamFile { version 2.0; format ascii; class dictionary; object blockMeshDict; }
scale 1;
vertices ((-35 0 -30) (75 0 -30) (75 35 -30) (-35 35 -30) (-35 0 35) (75 0 35) (75 35 35) (-35 35 35));
blocks (hex (0 1 2 3 4 5 6 7) (74 24 44) simpleGrading (1 1 1));
edges ();
boundary (
inlet { type patch; faces ((0 4 7 3)); }
outlet { type patch; faces ((1 2 6 5)); }
symmetry { type symmetryPlane; faces ((0 1 5 4)); }
farfield { type patch; faces ((3 7 6 2) (0 3 2 1) (4 5 6 7)); }
);
mergePatchPairs ();


Common mesh / system/snappyHexMeshDict
FoamFile { version 2.0; format ascii; class dictionary; object snappyHexMeshDict; }

castellatedMesh true; snap true; addLayers false;
geometry {
 aircraft_regions.stl {type triSurfaceMesh; name aircraft;}
 nearBody {type searchableBox; min (-7 -0.1 -1.5); max (8 9 7);}
 wake {type searchableBox; min (0 -0.1 -3); max (30 10 16);}
}
castellatedMeshControls {
 maxLocalCells 500000; maxGlobalCells 4000000; minRefinementCells 5;
 maxLoadUnbalance 0.1; nCellsBetweenLevels 4;
 features ();
 refinementSurfaces { aircraft {level (4 5); patchInfo {type wall; inGroups (airframe);} regions {
fuselage { level (6 6); patchInfo {type wall; inGroups (airframe fuselageGroup);} }
wing { level (7 7); patchInfo {type wall; inGroups (airframe wingGroup);} }
tail { level (7 7); patchInfo {type wall; inGroups (airframe tailGroup);} }
booms { level (6 6); patchInfo {type wall; inGroups (airframe boomsGroup);} }
nacelles { level (7 7); patchInfo {type wall; inGroups (airframe nacellesGroup);} }
gear { level (6 6); patchInfo {type wall; inGroups (airframe gearGroup);} }
 } } }
 resolveFeatureAngle 30;
 refinementRegions {
 nearBody {mode inside; levels ((1e15 3));}
 wake {mode inside; levels ((1e15 2));}
 aircraft {mode distance; levels ((0.08 5) (0.25 4) (0.8 3));}
 }
 locationInMesh (-20.123 10.123 10.123); allowFreeStandingZoneFaces true;
}
snapControls {
 nSmoothPatch 8; tolerance 1.4; nSolveIter 80; nRelaxIter 12;
 nFeatureSnapIter 12; implicitFeatureSnap true; explicitFeatureSnap false; multiRegionFeatureSnap false;
}
addLayersControls {
 relativeSizes false;
 layers {"aircraft.*" {nSurfaceLayers 5;}}
 expansionRatio 1.25; firstLayerThickness 0.0015; minThickness 0.0008;
 nGrow 0; featureAngle 60; slipFeatureAngle 30; nRelaxIter 5;
 nSmoothSurfaceNormals 4; nSmoothNormals 6; nSmoothThickness 10;
 maxFaceThicknessRatio 0.5; maxThicknessToMedialRatio 0.3; minMedialAxisAngle 90;
 nBufferCellsNoExtrude 2; nLayerIter 60;
}
meshQualityControls {
 #includeEtc "caseDicts/meshQualityDict"
 maxNonOrtho 60; maxBoundarySkewness 3; maxInternalSkewness 2.5; maxConcave 65; minDeterminant 0.002; minVolRatio 0.02;
 minVol 1e-13; minFaceWeight 0.08; nSmoothScale 4; errorReduction 0.75;
}
writeFlags (scalarLevels layerSets layerFields); mergeTolerance 1e-7;


Common mesh / system/meshQualityDict
FoamFile {version 2; format ascii; class dictionary; object meshQualityDict;}
#includeEtc "caseDicts/meshQualityDict"
maxNonOrtho 60; maxBoundarySkewness 3; maxInternalSkewness 2.5; minDeterminant 0.002; minFaceWeight 0.08; minVolRatio 0.02; minVol 1e-13;