CFD Online Logo CFD Online URL
www.cfd-online.com
[Sponsors]
Home > Forums > Software User Forums > OpenFOAM > OpenFOAM Running, Solving & CFD

Wingtip vortex OpenFoam. Error solving with simpleFoam

Register Blogs Members List Search Today's Posts Mark Forums Read

Reply
 
LinkBack Thread Tools Search this Thread Display Modes
Old   May 16, 2018, 15:08
Default Wingtip vortex OpenFoam. Error solving with simpleFoam
  #1
New Member
 
Join Date: May 2018
Posts: 1
Rep Power: 0
luram94 is on a distinguished road
Hi foamers.

I am simulating a wingtip vortex for a laminar, steady case.
I have adapted the Airfoil2D tutorial to my 3D case.
I am using a simulation type laminar that i've typed on the turbulenceProperties file.

My mesh is a wing of 0.1 chord enclosed on a prism. I've meshed it with PointWise.



I have checked the smallest cell of my mesh to adapt the deltaT for the courant number. The smallest cell size is "Minimum face area = 1.4231e-09". So I am trying different deltaT values but the error always happens on the same point.


Here you can see the mistake.


I hope someone could help me.
Thank you !!



luram94@Aspire-E5-574G:~/OpenFOAM/luram94-5.0/run/airFoil2D1$ simpleFoam
/*---------------------------------------------------------------------------*\
| ========= | |
| \\ / F ield | OpenFOAM: The Open Source CFD Toolbox |
| \\ / O peration | Version: 5.x |
| \\ / A nd | Web: www.OpenFOAM.org |
| \\/ M anipulation | |
\*---------------------------------------------------------------------------*/
Build : 5.x-197d9d3bf20a
Exec : simpleFoam
Date : May 16 2018
Time : 19:45:59
Host : "Aspire-E5-574G"
PID : 5766
I/O : uncollated
Case : /home/luram94/OpenFOAM/luram94-5.0/run/airFoil2D1
nProcs : 1
sigFpe : Enabling floating point exception trapping (FOAM_SIGFPE).
fileModificationChecking : Monitoring run-time modified files using timeStampMaster (fileModificationSkew 10)
allowSystemOperations : Allowing user-supplied system call operations

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

Create mesh for time = 0


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

Reading field p

Reading field U

Reading/calculating face flux field phi

Selecting incompressible transport model Newtonian
Selecting turbulence model type laminar
Selecting laminar stress model Stokes
No MRF models present

No finite volume options present


Starting time loop

Time = 0.0001

smoothSolver: Solving for Ux, Initial residual = 1, Final residual = 0.0695286, No Iterations 2
smoothSolver: Solving for Uy, Initial residual = 1, Final residual = 0.0254532, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 1, Final residual = 0.0654825, No Iterations 4
GAMG: Solving for p, Initial residual = 1, Final residual = 0.0943924, No Iterations 16
time step continuity errors : sum local = 9.32871e-09, global = -1.09984e-20, cumulative = -1.09984e-20
ExecutionTime = 0.24 s ClockTime = 0 s

Time = 0.0002

smoothSolver: Solving for Ux, Initial residual = 0.417036, Final residual = 0.0237835, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 0.525095, Final residual = 0.0355146, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 0.361729, Final residual = 0.0187467, No Iterations 4
GAMG: Solving for p, Initial residual = 0.994142, Final residual = 0.0944352, No Iterations 4
time step continuity errors : sum local = 2.68322e-07, global = -6.64015e-21, cumulative = -1.76385e-20
ExecutionTime = 0.32 s ClockTime = 0 s

Time = 0.0003

smoothSolver: Solving for Ux, Initial residual = 0.48106, Final residual = 0.0291823, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 0.592922, Final residual = 0.0163415, No Iterations 6
smoothSolver: Solving for Uz, Initial residual = 0.365147, Final residual = 0.0195021, No Iterations 4
GAMG: Solving for p, Initial residual = 0.989267, Final residual = 0.098107, No Iterations 65
time step continuity errors : sum local = 6.09575e-06, global = -2.51469e-21, cumulative = -2.01532e-20
ExecutionTime = 0.61 s ClockTime = 0 s

Time = 0.0004

smoothSolver: Solving for Ux, Initial residual = 0.633188, Final residual = 0.0383804, No Iterations 2
smoothSolver: Solving for Uy, Initial residual = 0.631868, Final residual = 0.0342176, No Iterations 2
smoothSolver: Solving for Uz, Initial residual = 0.544371, Final residual = 0.0420833, No Iterations 2
GAMG: Solving for p, Initial residual = 0.99557, Final residual = 0.0985544, No Iterations 22
time step continuity errors : sum local = 0.000284088, global = -7.5344e-20, cumulative = -9.54973e-20
ExecutionTime = 0.74 s ClockTime = 0 s

Time = 0.0005

smoothSolver: Solving for Ux, Initial residual = 0.503184, Final residual = 0.0360833, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 0.600972, Final residual = 0.0378856, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 0.580002, Final residual = 0.0347582, No Iterations 4
GAMG: Solving for p, Initial residual = 0.999452, Final residual = 0.0939822, No Iterations 17
time step continuity errors : sum local = 0.00724173, global = 6.35417e-19, cumulative = 5.39919e-19
ExecutionTime = 0.86 s ClockTime = 0 s

Time = 0.0006

smoothSolver: Solving for Ux, Initial residual = 0.494103, Final residual = 0.013902, No Iterations 4
smoothSolver: Solving for Uy, Initial residual = 0.45221, Final residual = 0.0124333, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 0.506377, Final residual = 0.0317716, No Iterations 4
GAMG: Solving for p, Initial residual = 0.992318, Final residual = 0.0991528, No Iterations 21
time step continuity errors : sum local = 0.191447, global = 6.35768e-18, cumulative = 6.8976e-18
ExecutionTime = 1 s ClockTime = 1 s

Time = 0.0007

smoothSolver: Solving for Ux, Initial residual = 0.524298, Final residual = 0.0290546, No Iterations 6
smoothSolver: Solving for Uy, Initial residual = 0.525085, Final residual = 0.0402515, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 0.929924, Final residual = 0.0688259, No Iterations 10
GAMG: Solving for p, Initial residual = 0.999893, Final residual = 0.0971346, No Iterations 10
time step continuity errors : sum local = 29.8918, global = -5.18405e-15, cumulative = -5.17715e-15
ExecutionTime = 1.1 s ClockTime = 1 s

Time = 0.0008

smoothSolver: Solving for Ux, Initial residual = 0.549428, Final residual = 0.0525383, No Iterations 2
smoothSolver: Solving for Uy, Initial residual = 0.535445, Final residual = 0.00941288, No Iterations 4
smoothSolver: Solving for Uz, Initial residual = 0.485405, Final residual = 0.00742206, No Iterations 4
GAMG: Solving for p, Initial residual = 0.89532, Final residual = 0.0826279, No Iterations 3
time step continuity errors : sum local = 294.428, global = -6.74072e-14, cumulative = -7.25843e-14
ExecutionTime = 1.16 s ClockTime = 1 s

Time = 0.0009

smoothSolver: Solving for Ux, Initial residual = 0.538549, Final residual = 0.0375504, No Iterations 6
smoothSolver: Solving for Uy, Initial residual = 0.572799, Final residual = 0.0172758, No Iterations 8
smoothSolver: Solving for Uz, Initial residual = 0.47479, Final residual = 0.0266104, No Iterations 8
GAMG: Solving for p, Initial residual = 3.30709e-05, Final residual = 2.99641e-06, No Iterations 12
time step continuity errors : sum local = 7.49553e+06, global = 1.44336e-08, cumulative = 1.44335e-08
ExecutionTime = 1.27 s ClockTime = 1 s

Time = 0.001

smoothSolver: Solving for Ux, Initial residual = 0.466723, Final residual = 0.0230642, No Iterations 46
smoothSolver: Solving for Uy, Initial residual = 0.471586, Final residual = 0.0297526, No Iterations 42
smoothSolver: Solving for Uz, Initial residual = 0.37227, Final residual = 0.0159206, No Iterations 48
GAMG: Solving for p, Initial residual = 1, Final residual = 0.0966592, No Iterations 6
time step continuity errors : sum local = 4.40691e+16, global = -60.8033, cumulative = -60.8033
ExecutionTime = 1.42 s ClockTime = 1 s

Time = 0.0011

smoothSolver: Solving for Ux, Initial residual = 0.400004, Final residual = 177.261, No Iterations 1000
smoothSolver: Solving for Uy, Initial residual = 0.428658, Final residual = 285.171, No Iterations 1000
smoothSolver: Solving for Uz, Initial residual = 0.445417, Final residual = 649.365, No Iterations 1000
#0 Foam::error:rintStack(Foam::Ostream&) at ??:?
#1 Foam::sigFpe::sigHandler(int) at ??:?
#2 ? in "/lib/x86_64-linux-gnu/libc.so.6"
#3 Foam::GAMGSolver::scale(Foam::Field<double>&, Foam::Field<double>&, Foam::lduMatrix const&, Foam::FieldField<Foam::Field, double> const&, Foam::UPtrList<Foam::lduInterfaceField const> const&, Foam::Field<double> const&, unsigned char) const at ??:?
#4 Foam::GAMGSolver::Vcycle(Foam::PtrList<Foam::lduMa trix::smoother> const&, Foam::Field<double>&, Foam::Field<double> const&, Foam::Field<double>&, Foam::Field<double>&, Foam::Field<double>&, Foam::Field<double>&, Foam::Field<double>&, Foam::PtrList<Foam::Field<double> >&, Foam::PtrList<Foam::Field<double> >&, unsigned char) const at ??:?
#5 Foam::GAMGSolver::solve(Foam::Field<double>&, Foam::Field<double> const&, unsigned char) const at ??:?
#6 Foam::fvMatrix<double>::solveSegregated(Foam::dict ionary const&) at ??:?
#7 Foam::fvMatrix<double>::solve(Foam::dictionary const&) at ??:?
#8 Foam::fvMatrix<double>::solve() at ??:?
#9 ? at ??:?
#10 __libc_start_main in "/lib/x86_64-linux-gnu/libc.so.6"
#11 ? at ??:?
luram94 is offline   Reply With Quote

Old   October 19, 2018, 12:53
Default
  #2
Senior Member
 
Klaus
Join Date: Mar 2009
Posts: 149
Rep Power: 12
klausb is on a distinguished road
Hello,

it's usually worth to try a tolerance for p lower than that of the other values e.g.

Code:
solvers
{
    p
    {
        solver                PCG;
        preconditioner   FDIC;
        tolerance           1e-08;
        relTol                0;
    }

    U
    {
          solver                PBiCGStab; 
          preconditioner   DILU;
          tolerance           1e-7;
           relTol                 0.01;
    }
...
But actually to give real advice, you should provide more information about your mesh including the number of cells around your airfoil (try 300 cells chord wise) and the other mesh parameters used. Did you use checkMesh and renumberMesh? How many cells are there?

What's your AOA, reynolds number etc.?

Could you post your case or at least some key files including fvSolution, fvSchemes and controlDict?

The setup of the airFoil2D case appears rather "minimalistic" especially the fvSchemes.
klausb is offline   Reply With Quote

Reply

Tags
laminar flow, simplefoam, solve, solve time, wingtip

Thread Tools Search this Thread
Search this Thread:

Advanced Search
Display Modes

Posting Rules
You may not post new threads
You may not post replies
You may not post attachments
You may not edit your posts

BB code is On
Smilies are On
[IMG] code is On
HTML code is Off
Trackbacks are Off
Pingbacks are On
Refbacks are On


Similar Threads
Thread Thread Starter Forum Replies Last Post
OpenFOAM 4.0 Released CFDFoundation OpenFOAM Announcements from OpenFOAM Foundation 2 October 6, 2017 06:40
OpenFOAM Training, London, Chicago, Munich, Sep-Oct 2015 cfd.direct OpenFOAM Announcements from Other Sources 2 August 31, 2015 14:36
Frequently Asked Questions about Installing OpenFOAM wyldckat OpenFOAM Installation 0 January 1, 2014 20:21
New OpenFOAM Forum Structure jola OpenFOAM 2 October 19, 2011 07:55
wingtip vortex Rooney Siemens 2 January 9, 2009 08:58


All times are GMT -4. The time now is 21:31.