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-   -   Problem with Aerofoam for OF1.7.1 (http://www.cfd-online.com/Forums/openfoam-solving/86910-problem-aerofoam-of1-7-1-a.html)

Emilie April 6, 2011 03:49

Problem with Aerofoam for OF1.7.1
 
Hello everybody,

I'm trying to use the solver AeroFoam with the 1.7.1 version of OF; it's part of an important project for my study. I downloaded the Aerofoam files at :
https://sourceforge.net/projects/aerofoam/files/Source/
And now I want to test this solver with a tutorial case : the oblique shock.
However, (after 'BlockMesh'), when I launch AeroFoam, I have :


-------------------------------------------------------------

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

Create mesh for time = 0

========================================
Reading Thermodynamic Properties...
========================================
gamma [-] = 1.4
Pr [-] = 0.72
R [J/KgK] = 287.05
Cp [J/KgK] = 717.625
Cv [J/KgK] = 1004.67
----------------------------------------

========================================
Reading Initial Conditions...
========================================
Reading field p
Reading field T
Reading field U
----------------------------------------
Creating conservative variables at t^(k)
Creating conservative variables at t^(k-1)
Creating conservative variables at t^(k-2)
Creating conservative variables fluxes at t^(k)
Creating primitive variables gradient fields (optional)
----------------------------------------

========================================
Creating Mesh Connectivity...
========================================
Using adaptive algorithm...
id_LL_i7290SIZE3510Loop on Internal Faces...
i=0i=1i=2i=3i=4i=5i=6i=7i=8i=9i=10i=11i=1

until i=3509
Loop on Boundary Faces...
----------------------------------------

========================================
Mesh
========================================
# of Faces = 3510
# of Cells = 1800
# of BndPatch = 5
0) inlet @ top
1) supersonicInlet @ inlet
2) extrapolatedOutlet @ outlet
3) symmetryPlane @ bottom
4) empty @ frontAndBack
----------------------------------------

========================================
Numerical Scheme
========================================
flowType = Euler
timeScheme = RK2
CourantMax = 0.1
CourantSteps = 25
MonotoneFlux = Roe
HighResFlux = LW
fluxLimiter = VL
entropyFix = HH2
extrapolateBC = 1
residualNorm = L1
minResidual = -1
----------------------------------------
Does everything look fine? [y] to continue [n] otherwise

-------------------------------------------------------------
I type yes and get :

-------------------------------------------------------------
blf fx i=1
...
blf fx i=3509
#0 Foam::error::printStack(Foam::Ostream&) in "/opt/openfoam171/lib/linux64GccDPOpt/libOpenFOAM.so"
#1 Foam::sigSegv::sigSegvHandler(int) in "/opt/openfoam171/lib/linux64GccDPOpt/libOpenFOAM.so"
#2 in "/lib/libc.so.6"
#3
at Foam::GeometricField<Foam::Vector<double>, Foam::fvsPatchField, Foam::surfaceMesh>*, Foam::GeometricField<double, Foam::fvsPatchField, Foam::surfaceMesh>*, Foam::word, Foam::word, Foam::word, Foam::word, double)
#4
in "/home/emilie/OpenFOAM/bruno-1.7.1/applications/bin/linux64GccDPOpt/AeroFoam"
#5 __libc_start_main in "/lib/libc.so.6"
#6
in "/home/emilie/OpenFOAM/bruno-1.7.1/applications/bin/linux64GccDPOpt/AeroFoam"
Segmentation fault

-------------------------------------------------------------

Does anyone has an idea why I have this error ?:confused:

Thank you very much for your help ! :)

Emilie

Solarberiden June 17, 2011 03:35

could you please rebuild your openfoam in debug mode and repost the error message? The final error message you posted didn't bring forwards any location about the error position information, which is a little bit difficult for other "depanner" , LOL.
by the way, the author of the version you are using and downloading from sourceforge JLight2010 had mentioned that
http://www.cfd-online.com/Forums/ope...free-code.html
he is not sure about the code correctness, further discuss would be depending your reply, I have tried some examples including the OneraM6 case and YF-17 case.

Rachit June 21, 2011 06:17

Stuck!!
 
Hi everyone!:)

I am a new of OpenFOAM and hence AeroFoam as well. In order to get familiar with it, I went to the following website and downloaded the Oblique Shock Test problem:

http://www.aero.polimi.it/freecase/?...:Oblique_shock

After uncompressing the folder, I tried to run it, but the following came on the terminal:

This is a start/*---------------------------------------------------------------------------*\
| ========= | |
| \\ / F ield | OpenFOAM: The Open Source CFD Toolbox |
| \\ / O peration | Version: 1.6 |
| \\ / A nd | Web: www.OpenFOAM.org |
| \\/ M anipulation | |
\*---------------------------------------------------------------------------*/
Build : 1.6-53b7f692aa41
Exec : AeroFoam
Date : Jun 21 2011
Time : 16:02:27
Host : rachit-desktop
PID : 5378
Case : /home/rachit/OpenFOAM/OpenFOAM-1.6/foam_run/compressible/ObliqueShock_B/ObliqueShock_B
nProcs : 1
SigFpe : Enabling floating point exception trapping (FOAM_SIGFPE).

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

Create mesh for time = 0

// using new solver syntax:
cellDisplacement
{
solver PCG;
preconditioner DIC;
tolerance 1e-08;
relTol 0;
}

========================================
Reading Thermodynamic Properties...
========================================
gamma [-] = 1.4
Pr [-] = 0.72
R [J/KgK] = 287.05
Cp [J/KgK] = 717.625
Cv [J/KgK] = 1004.67
----------------------------------------

========================================
Reading Initial Conditions...
========================================
Reading field p
Reading field T
Reading field U
----------------------------------------
Creating conservative variables at t^(k)
Creating conservative variables at t^(k-1)
Creating conservative variables at t^(k-2)
Creating conservative variables fluxes at t^(k)
Creating primitive variables gradient fields (optional)
----------------------------------------

========================================
Creating Mesh Connectivity...
========================================
Using adaptive algorithm...
id_LL_i6500SIZE3100Loop on Internal Faces...


Nothing happens beyond this, as in the process is still continuing but no progress is being made.:confused:

Could anyone please tell me what mistake I am making?

Thanks in advance!

Rachit

trantoan2008 September 27, 2011 04:15

Hi All,

I had the same problem like you when I tried to use AeroFoam solver to test that case. Is there anybody treat this problem?

aerothermal December 5, 2011 15:43

I had same problem here when running the Onera M6 wing test case downloaded from AeroFoam site and using AeroFoam for OF1.7.1.

Quote:

Originally Posted by Emilie (Post 302432)
Hello everybody,

I'm trying to use the solver AeroFoam with the 1.7.1 version of OF; it's part of an important project for my study. I downloaded the Aerofoam files at :
https://sourceforge.net/projects/aerofoam/files/Source/
And now I want to test this solver with a tutorial case : the oblique shock.
However, (after 'BlockMesh'), when I launch AeroFoam, I have :


-------------------------------------------------------------

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

Create mesh for time = 0

========================================
Reading Thermodynamic Properties...
========================================
gamma [-] = 1.4
Pr [-] = 0.72
R [J/KgK] = 287.05
Cp [J/KgK] = 717.625
Cv [J/KgK] = 1004.67
----------------------------------------

========================================
Reading Initial Conditions...
========================================
Reading field p
Reading field T
Reading field U
----------------------------------------
Creating conservative variables at t^(k)
Creating conservative variables at t^(k-1)
Creating conservative variables at t^(k-2)
Creating conservative variables fluxes at t^(k)
Creating primitive variables gradient fields (optional)
----------------------------------------

========================================
Creating Mesh Connectivity...
========================================
Using adaptive algorithm...
id_LL_i7290SIZE3510Loop on Internal Faces...
i=0i=1i=2i=3i=4i=5i=6i=7i=8i=9i=10i=11i=1

until i=3509
Loop on Boundary Faces...
----------------------------------------

========================================
Mesh
========================================
# of Faces = 3510
# of Cells = 1800
# of BndPatch = 5
0) inlet @ top
1) supersonicInlet @ inlet
2) extrapolatedOutlet @ outlet
3) symmetryPlane @ bottom
4) empty @ frontAndBack
----------------------------------------

========================================
Numerical Scheme
========================================
flowType = Euler
timeScheme = RK2
CourantMax = 0.1
CourantSteps = 25
MonotoneFlux = Roe
HighResFlux = LW
fluxLimiter = VL
entropyFix = HH2
extrapolateBC = 1
residualNorm = L1
minResidual = -1
----------------------------------------
Does everything look fine? [y] to continue [n] otherwise

-------------------------------------------------------------
I type yes and get :

-------------------------------------------------------------
blf fx i=1
...
blf fx i=3509
#0 Foam::error::printStack(Foam::Ostream&) in "/opt/openfoam171/lib/linux64GccDPOpt/libOpenFOAM.so"
#1 Foam::sigSegv::sigSegvHandler(int) in "/opt/openfoam171/lib/linux64GccDPOpt/libOpenFOAM.so"
#2 in "/lib/libc.so.6"
#3
at Foam::GeometricField<Foam::Vector<double>, Foam::fvsPatchField, Foam::surfaceMesh>*, Foam::GeometricField<double, Foam::fvsPatchField, Foam::surfaceMesh>*, Foam::word, Foam::word, Foam::word, Foam::word, double)
#4
in "/home/emilie/OpenFOAM/bruno-1.7.1/applications/bin/linux64GccDPOpt/AeroFoam"
#5 __libc_start_main in "/lib/libc.so.6"
#6
in "/home/emilie/OpenFOAM/bruno-1.7.1/applications/bin/linux64GccDPOpt/AeroFoam"
Segmentation fault

-------------------------------------------------------------

Does anyone has an idea why I have this error ?:confused:

Thank you very much for your help ! :)

Emilie



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