[hhh]

hai friends,

i am doing 2d naca0012 airfoil analysis for turbulent case using simplefoam for angle of attack 2. I try to convert results in VTK format,but i got error like this

file: /home/kum/freefoam-user-doc/tutorials/incompressible/simpleFoam/airfoil/2/0/nut::boundaryField::airfoil from line 37 to line 38.

From function fvPatchField<Type>::New(const fvPatch&, const DimensionedField<Type, volMesh>&, const dictionary&)
in file /build/buildd/freefoam-0.1.0+dfsg/obj-x86_64-linux-gnu/include/finiteVolume/../../../src/finiteVolume/fields/fvPatchFields/fvPatchField/newFvPatchField.C at line 110.

FOAM exiting

kindly guide me

[wyldckat]

Greetings Kumar,

This isn't enough information to help you

Can you share the file "0/nut"?
Or can you post what is on the lines 37 and 38 of this file?

And just to confirm, did you run simpleFoam with success?

Best regards,
Bruno

PS: I moved your post to a new thread, since the error is different from the other thread.

[hhh]

Thanks wyldckat to coming forward to help me.

I successfully run simplefoam and got results for all, i am doing angle of attack of 0,2,4,6,8,10.but problem is to convert VTK format.please see my attached file.

[wyldckat]

Hi Kumar,

OK, the problem seems to be that foamToVTK does not recognise the boundary condition "nutSpalartAllmarasWallFunction".

If it were OpenFOAM instead of FreeFOAM, the following steps should work:

1. Edit the file "system/controlDict".
2. Add this line to it:
   

   libs ("libincompressibleRASModels.so");

3. Save and close the file.
4. Try foamToVTK once again.

You can these steps with FreeFOAM, but you might have to adjust the name of the library name.

Best regards,
Bruno

[hhh]

Hai Bruno,

I unstall freefoam,because again its give the same error, so i install ubuntu 11.10 with openfoam 2.1. but I got this error during mesh conversation fluentMeshtoFoam,please tell me what i have to do?

"version to version i get confused,this is final one i install[ubuntu 11.10 with openfoam 2.1]"

toshiba@ubuntu:~/openfoam210/tutorials/incompressible/simpleFoam/airFoil2D$ fluentMeshToFoam naca0012.msh
fluentMeshToFoam: command not found

[wyldckat]

Hi Kumar,

Which exact OpenFOAM installation instructions did you follow?

Best regards,
Bruno

[hhh]

Hi Bruno, i install ubuntu 11.10 with openfoam version 2.1.0

LINK: http://www.openfoam.org/archive/2.1....oad/ubuntu.php

[wyldckat]

Hi Kumar,

What does the file "~/.bashrc" have near the end of the file? Does it only have the following line?

source /opt/openfoam210/etc/bashrc

Or is there still any reference to FreeFOAM?

And what about the following command:

icoFoam -help

Does it show anything?

Best regards,
Bruno

[hhh]

Thanks Bruno,that step i forgot to did. I run cavity,right now everything works fine.

For airfoil i got another error like this, i did any mistake please let me know

/*---------------------------------------------------------------------------*\
| ========= | |
| \\ / F ield | OpenFOAM: The Open Source CFD Toolbox |
| \\ / O peration | Version: 2.1.0 |
| \\ / A nd | Web: www.OpenFOAM.org |
| \\/ M anipulation | |
\*---------------------------------------------------------------------------*/
Build : 2.1.0-0bc225064152
Exec : fluentMeshToFoam naca0012.msh
Date : Jun 11 2013
Host : "ubuntu"
fileName::stripInvalid() called for invalid fileName /home/toshiba/OpenFOAM/toshiba-2.1.0/run/tutorials/incompressible/simpleFoam/UntitledFolder/airFoil2D
For debug level (= 2) > 1 this is considered fatal
Aborted
toshiba@ubuntu:~/OpenFOAM/toshiba-2.1.0/run/tutorials/incompressible/simpleFoam/Untitled Folder/airFoil2D$

[hhh]

hi bruno, i got the mistake, i change the UntitledFolder to ku, now its work fine, during run the simple foam i got this,

what ever i mention in red colour it shows any error?

toshiba@ubuntu:~/OpenFOAM/toshiba-2.1.0/run/tutorials/incompressible/simpleFoam/ku/airFoil2D$ simpleFoam
/*---------------------------------------------------------------------------*\
| ========= | |
| \\ / F ield | OpenFOAM: The Open Source CFD Toolbox |
| \\ / O peration | Version: 2.1.0 |
| \\ / A nd | Web: www.OpenFOAM.org |
| \\/ M anipulation | |
\*---------------------------------------------------------------------------*/
Build : 2.1.0-0bc225064152
Exec : simpleFoam
Date : Jun 11 2013
Time : 14:42:35
Host : "ubuntu"
Case : /home/toshiba/OpenFOAM/toshiba-2.1.0/run/tutorials/incompressible/simpleFoam/ku/airFoil2D
nProcs : 1
sigFpe : Enabling floating point exception trapping (FOAM_SIGFPE).
fileModificationChecking : Monitoring run-time modified files using timeStampMaster
allowSystemOperations : Disallowing user-supplied system call operations

// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //
Create time

Create mesh for time = 0

Reading field p

Reading field U

Reading/calculating face flux field phi

Selecting incompressible transport model Newtonian
Selecting RAS turbulence model SpalartAllmaras
SpalartAllmarasCoeffs
{
sigmaNut 0.66666;
kappa 0.41;
Cb1 0.1355;
Cb2 0.622;
Cw2 0.3;
Cw3 2;
Cv1 7.1;
Cv2 5;
}

No field sources present


SIMPLE: convergence criteria
field p tolerance 1e-05
field U tolerance 1e-05
field nuTilda tolerance 1e-05


Starting time loop

Time = 1

smoothSolver: Solving for Ux, Initial residual = 0.999993, Final residual = 0.0558381, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 1, Final residual = 0.0760732, No Iterations 2
GAMG: Solving for p, Initial residual = 1, Final residual = 0.0991895, No Iterations 39
time step continuity errors : sum local = 0.00119979, global = 6.26709e-16, cumulative = 6.26709e-16
smoothSolver: Solving for nuTilda, Initial residual = 0.999999, Final residual = 0.0701398, No Iterations 4
ExecutionTime = 36.7 s ClockTime = 37 s

forces output:
forces(pressure,viscous)((257697 5.20299e+06 7.66604e-16),(6.53254 1.33905 -1.89121e-21))
moment(pressure,viscous)((-3.39084e-17 -1.06156e-16 2.50963e+06),(4.47879e-23 -2.14236e-22 0.66735))

forceCoeffs output:
Cm = 901.996
Cd = 415.85
Cl = 1857.68
Cl(f) = 1830.84
Cl(r) = 26.8427

Time = 2

smoothSolver: Solving for Ux, Initial residual = 0.623192, Final residual = 0.0517858, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 0.445407, Final residual = 0.0284221, No Iterations 4
GAMG: Solving for p, Initial residual = 0.711508, Final residual = 0.0608906, No Iterations 11
time step continuity errors : sum local = 0.000802196, global = 1.48748e-15, cumulative = 2.11418e-15
smoothSolver: Solving for nuTilda, Initial residual = 0.258696, Final residual = 0.0187245, No Iterations 4
ExecutionTime = 45.88 s ClockTime = 46 s

forces output:
forces(pressure,viscous)((168327 3.88357e+06 2.72499e-16),(23.6262 2.65695 -2.24632e-21))
moment(pressure,viscous)((-2.10668e-17 -5.5126e-17 1.89813e+06),(5.34685e-23 -6.75307e-22 1.37948))

forceCoeffs output:
Cm = 682.213
Cd = 301.9
Cl = 1385.1
Cl(f) = 1374.76
Cl(r) = 10.3358


I hope everthing is fine its keep on running like this i got cl,cd,cm, please let me what i mention in red colour.

[wyldckat]

Hi Kumar,

I'll try to answer at least some of these questions on your other thread, where you've asked them again: http://www.cfd-online.com/Forums/ope...hat-means.html

Best regards,
Bruno