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Drag Components in OpenFoam

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Old   March 28, 2017, 03:14
Default Drag Components in OpenFoam
  #1
adr
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anthony
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Hello partners;

I'm new in OpenFoam and I would like to know how to calculate the components of the
drag coefficient, the viscous component (Cdv) and the pressure component (Cdp).

I have this postprocessing, for example for a NACA profile with angle of attack 5:

////////////////////////////////////////////////////////

# Force coefficients
# liftDir : (-8.715574e-02 9.961947e-01 0.000000e+00)
# dragDir : (9.961947e-01 8.715574e-02 0.000000e+00)
# pitchAxis : (0.000000e+00 0.000000e+00 1.000000e+00)
# magUInf : 1.000000e+00
# lRef : 1.000000e+00
# Aref : 1.000000e+00
# CofR : (2.500000e-01 0.000000e+00 0.000000e+00)
# Time Cm Cd Cl Cl(f) Cl(r)

50 -3.381931e-02 2.525614e-02 1.507514e-01 4.155637e-02 1.091950e-01
100 2.877479e-02 2.730709e-02 3.181085e-01 1.878291e-01 1.302795e-01


////////////////////////////////////////////////////////////
# Forces
# CofR : (2.500000e-01 0.000000e+00 0.000000e+00)
# Time forces(pressure viscous porous) moment(pressure viscous porous)

50 ((-4.093538e-03 7.591890e-02 1.893935e-21) (1.010413e-02 2.705541e-04 -1.629982e-19) (0.000000e+00 0.000000e+00 0.000000e+00)) ((-3.795945e-02 -2.046769e-03 -1.683966e-02) (-1.352770e-04 5.052067e-03 -6.999131e-05) (0.000000e+00 0.000000e+00 0.000000e+00))

100 ((-6.673421e-03 1.594468e-01 1.740584e-21) (6.412519e-03 1.921648e-04 2.494450e-20) (0.000000e+00 0.000000e+00 0.000000e+00)) ((-7.972341e-02 -3.336711e-03 1.443917e-02) (-9.608239e-05 3.206260e-03 -5.177497e-05) (0.000000e+00 0.000000e+00 0.000000e+00))

/////////////////////////////////////////////////////////////

Furthemore I have this parameters for the simulation:

rho rhoInf; // Indicates incompressible
log true;
rhoInf 1; // Redundant for incompressible
liftDir (0 1 0);
dragDir (1 0 0);
CofR (0.25 0 0); // Center of rotation for Cm Calculation
pitchAxis (0 0 1); // Axis of rotation for Cm Calculation
magUInf 1;
lRef 1; // Chord
Aref 1; // Chord*Span (our cell width is 1!)
}

////////////////////////////////////////////////////////

Can anyone help me calculate the components of the drag?
THANKS A LOT.
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Old   March 29, 2017, 10:58
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Hi,

Just use the output from forces to calculate your separated components:

Cdv= 2*Fvx/(rho*V²*A)
Cdp= 2*Fpx/(rho*V²*A)

Where Fp is the first entry in forces
Quote:
(-4.093538e-03 7.591890e-02 1.893935e-21)
, meaning Fpx = -4.093538e-03, Fpy = 7.591890e-02 and a very small Fpz due to machine tolerance for time = 50.

Similar for Fv =
Quote:
(1.010413e-02 2.705541e-04 -1.629982e-19)
for time = 50.

You probably want to write a script or do this with a spreadsheat program or whatever.

Cheers,
Tom
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Old   March 29, 2017, 13:34
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OF can calculate the drac coefficient for you. Simply include in controlDict lines like

Code:
functions
{
    forces
    {
        type            forceCoeffs;
        functionObjectLibs ( "libforces.so" );
        outputControl   timeStep;
        outputInterval  1;
        patches         ( cylinder );
        pName           p;
        UName           U;
        rhoName         rhoInf;
        log             true;
        rhoInf          1;
        liftDir         (0 1 0);
        dragDir         (1 0 0);
        CofR            (-0.5 0 0);
        pitchAxis       (0 1 0);
        magUInf         1;
        lRef            1;
        Aref            1;
    }
}
You have to adapt it to your case.

The result is in the postProcessing/forces folder.
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Old   March 30, 2017, 06:32
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Hi Tom;

Thank you very much for answering so quickly.

I finally did what you told me and using a spreadsheet to automate all the angles of attack.

Runs perfectly

Thanks!!!
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Old   March 30, 2017, 06:35
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Hi Piu58;

Thanks for your reply, I will try to adapt the code for my case to simplify the postprocessing.

Code:
functions
{
    forces
    {
        type            forceCoeffs;
        functionObjectLibs ( "libforces.so" );
        outputControl   timeStep;
        outputInterval  1;
        patches         ( cylinder );
        pName           p;
        UName           U;
        rhoName         rhoInf;
        log             true;
        rhoInf          1;
        liftDir         (0 1 0);
        dragDir         (1 0 0);
        CofR            (-0.5 0 0);
        pitchAxis       (0 1 0);
        magUInf         1;
        lRef            1;
        Aref            1;
    }
}
Thanks!!!
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Old   March 29, 2020, 03:17
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Hi,

This seems to be a thread I have been looking for. Can anybody suggest how to calculate the viscous and pressure drag separately for flow over a cylinder?

I am simulating a 2D case in pisoFoam. I have copied the code to controlDict and run the case. In postProcessing/forceCoefficients, I get the drag coefficient for each deltaT whereas I need the viscous and pressure components. I understand it is possible to calculate these components using ParaView which I am not sure about.

I would be grateful to have your suggestions.

Thank you
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Old   March 29, 2020, 10:54
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Hi,

The forceCoeff functionObject does not always print this out, use the forces and calculate the coefficients yourself as explained in the second post.

In ParaView you would need to have the wallShearStress and the pressure to calculate the viscous and pressure force per patch, use integrate variables to get the correct forces. If your case is laminar and you do not have the wallShearStress available you may be able to calculate the wallNormal gradient in ParaView and use that to get the viscous force instead.

If you case runs quickly however I would encourage you to use the forces option and parse that file with a script to get the pressure and viscous coefficients.

Cheers,
Tom
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Old   March 29, 2020, 12:26
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Hi Tom,

Many thanks for the swift response. I understand you are pointing towards including a script in controlDict which can print the coefficients directly(please correct me if wrong). If that is the case, I presume such a script is not readily available in OF hence, I need to manipulate the source code. If you have come across any such scripts, please share. As you said, am simulating laminar cases.
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Old   March 30, 2020, 03:57
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Hi,

No this is a script you write yourself, no OpenFOAM code. It can be python, bash, or simply copying the fields into a spreadsheat and work on the data there.

You have the resulting data in some format, but you need it in a different format. You need to find something that works best for you, I am just giving you some ideas.

Hope this helps,
Tom
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Old   February 8, 2021, 04:47
Default edit drag coefficients
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Hi there, Id like to edit the drag coefficients in a solver, to represent microplastics. Is this possible?
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