# Problem with Aerofoam for OF1.7.1

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 April 6, 2011, 03:49 Problem with Aerofoam for OF1.7.1 #1 New Member   Emilie Garnier Join Date: Mar 2011 Location: Toulouse Posts: 3 Rep Power: 6 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:rintStack(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::fvsPatchField, Foam::surfaceMesh>*, Foam::GeometricField*, 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 ? Thank you very much for your help ! Emilie aerothermal likes this.

 June 17, 2011, 03:35 #2 New Member   TCH Join Date: Jul 2010 Location: Beijing City Posts: 15 Rep Power: 7 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 hypersonic cfd free code??? 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.

 September 27, 2011, 04:15 #4 Member   ThanhToan Join Date: Sep 2010 Posts: 47 Rep Power: 6 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?

December 5, 2011, 15:43
#5
Senior Member

Guilherme da Silva
Join Date: Aug 2010
Location: Sao Paulo - Brazil
Posts: 105
Rep Power: 6
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 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:rintStack(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::fvsPatchField, Foam::surfaceMesh>*, Foam::GeometricField*, 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 ? Thank you very much for your help ! Emilie

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