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Low Mach number wing/body junction convergence

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Old   September 15, 2014, 06:56
Question Low Mach number wing/body junction convergence
  #1
Zen
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Zeno
Join Date: Sep 2013
Location: Delft, The Netherlands
Posts: 63
Rep Power: 9
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Hello Everybody,

I am trying to simulate a naca 0015 wing attached perpendicularly to a flat plate.
The Mach number is ~0.1 and I am using the compressible solver.
My stopping criterion is based on the reduction of the residual of 4 orders of magnitude.
I am using a coarse mesh with 7*10^5 cells.

However, I have problems with the convergence.
Is it because I am using the compressible solver ?( I tried to use the incompressible one and it still doesn't converge).
Or is there a problem with the settings of my configuration file?

Attached are a plot of the residuals, an image of the mesh and a file containing the info specified in the configuration file and the error I get after ca. 30000 iterations.

Any help is appreciated.

Thanks,

Z

Code:
------------------------ Physical case definition -----------------------
Compressible RANS equations.
Turbulence model: Spalart Allmaras
Mach number: 0.098.
Angle of attack (AoA): 6 deg, and angle of sideslip (AoS): 0 deg.
Reynolds number: 762000.
No restart solution, use the values at infinity (freestream).
The reference length/area will be computed using y(2D) or z(3D) projection.
The reference length (moment computation) is 0.34.
Reference origin (moment computation) is (0.25, 0, 0).
Surface(s) where the force coefficients are evaluated: wing.
Surface(s) plotted in the output file: wing.
Input mesh file name: naca0015_rotated.su2

---------------------- Space numerical integration ----------------------
Roe solver for the flow inviscid terms.
Second order integration with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 10. 
The reference element size is: 0.34. 
Scalar upwind solver (first order) for the turbulence model.
First order integration.
Average of gradients with correction (viscous flow terms).
Piecewise constant integration of the flow source terms.
Average of gradients with correction (viscous turbulence terms).
Piecewise constant integration of the turbulence model source terms.
Gradient computation using Green-Gauss theorem.

---------------------- Time numerical integration -----------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
CFL ramp definition. factor: 1.1, every 1000 iterations, with a limit of 10.
Courant-Friedrichs-Lewy number:        1
Euler implicit time integration for the turbulence model.

------------------------- Convergence criteria --------------------------
Maximum number of iterations: 999999.
Reduce the density residual 5 orders of magnitude.
The minimum bound for the density residual is 10^(-10).
Start convergence criteria at iteration 10.

-------------------------- Output information ---------------------------
Writing a flow solution every 250 iterations.
Writing the convergence history every 1 iterations.
The output file format is Tecplot ASCII (.dat).
Convergence history file name: history.
Surface flow coefficients file name: surface_flow.
Flow variables file name: flow.
Restart flow file name: restart_flow.dat.

------------------- Config file boundary information --------------------
Far-field boundary marker(s): farfield.
Symmetry plane boundary marker(s): symmetry.
Constant heat flux wall boundary marker(s): wing, flatplate.

---------------------- Read grid file information -----------------------
Three dimensional problem.
727478 interior elements including halo cells. 
[n12-04:07091] 47 more processes have sent help message help-mpi-btl-base.txt / btl:no-nics
[n12-04:07091] Set MCA parameter "orte_base_help_aggregate" to 0 to see all help / error messages
727478 hexahedra.
677150 points, and 156763 ghost points.

------------------------- Geometry Preprocessing ------------------------
Setting point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
Identifying edges and vertices.
Computing centers of gravity.
Setting the control volume structure.
Volume of the computational grid: 370.
Searching for the closest normal neighbors to the surfaces.
Compute the surface curvature.
Max K: 0. Mean K: 0. Standard deviation K: 0.

------------------------- Solver Preprocessing --------------------------
Computing wall distances.
Area projection in the z-plane = 0.995.
Viscous flow: Computing pressure using the ideal gas law
based on the free-stream temperature and a density computed
from the Reynolds number.
Note: Negative pressure, temperature or density is not allowed!
Force coefficients computed using free-stream values.
-- Input conditions:
Specific gas constant: 287.058 N.m/kg.K.
Free-stream pressure: 99463.3 Pa.
Free-stream temperature: 288.15 K.
Free-stream density: 1.20247 kg/m^3.
Free-stream velocity: (33.1664, 0, 3.48593) m/s. Magnitude: 33.3491 m/s.
Free-stream total energy per unit mass: 207345 m^2/s^2.
Free-stream viscosity: 1.7893e-05 N.s/m^2.
Free-stream turb. kinetic energy per unit mass: 4.17061 m^2/s^2.
Free-stream specific dissipation: 28028 1/s.
-- Reference values:
Reference specific gas constant: 1 N.m/kg.K.
Reference pressure: 1 Pa.
Reference temperature: 1 K.
Reference density: 1 kg/m^3.
Reference velocity: 1 m/s.
Reference energy per unit mass: 1 m^2/s^2.
Reference viscosity: 1 N.s/m^2.
-- Resulting non-dimensional state:
Mach number (non-dim): 0.098
Reynolds number (non-dim): 762000. Re length: 0.34 m.
Specific gas constant (non-dim): 287.058
Free-stream temperature (non-dim): 288.15
Free-stream pressure (non-dim): 99463.3
Free-stream density (non-dim): 1.20247
Free-stream velocity (non-dim): (33.1664, 0, 3.48593). Magnitude: 33.3491
Free-stream total energy per unit mass (non-dim): 207345
Free-stream viscosity (non-dim): 1.7893e-05
Free-stream turb. kinetic energy (non-dim): 4.17061
Free-stream specific dissipation (non-dim): 28028

Initialize jacobian structure (Navier-Stokes). MG level: 0.
Initialize jacobian structure (SA model).

------------------------------ Begin Solver -----------------------------

 Maximum residual: -1.25842, located at point 41549.

 Iter    Time(s)      Res[Rho]       Res[nu]   CLift(Total)   CDrag(Total)
    0   1.590721     -3.210747     -5.593713       1.565292       1.150936
[...]
38618   1.908126     -7.419505     -6.272192       0.632451       0.035221
38619   1.908131     -7.419517     -6.272200       0.632451       0.035221
CSysSolve::modGramSchmidt: w[i+1] = NaN
CSysSolve::modGramSchmidt: w[i+1] = NaN
terminate called after throwing an instance of 'CSysSolve::modGramSchmidt: w[i+1] = NaN
terminate called after throwing an instance of 'int'
CSysSolve::modGramSchmidt: w[i+1] = NaN
CSysSolve::modGramSchmidt: w[i+1] = NaN
CSysSolve::modGramSchmidt: w[i+1] = NaN
CSysSolve::modGramSchmidt: w[i+1] = NaN
int'
[n12-04:07125] *** Process received signal ***
[n12-04:07125] Signal: Aborted (6)
[n12-04:07125] Signal code:  (-6)
CSysSolve::modGramSchmidt: w[i+1] = NaN
terminate called after throwing an instance of 'int'
[...]
[n12-04:07137] *** Process received signal ***
[n12-04:07137] Signal: Aborted (6)
[n12-04:07137] Signal code:  (-6)
[n12-04:07114] *** Process received signal ***
[n12-04:07114] Signal: Aborted (6)
[n12-04:07114] Signal code:  (-6)
[n12-04:07131] [ 0] /lib64/libpthread.so.0(+0xf710) [0x2b3c9d4af710]
[n12-04:07131] [ 1] /lib64/libc.so.6(gsignal+0x35) [0x2b3c9d6f2925]
[n12-04:07131] [ 2] /lib64/libc.so.6(abort+0x175) [0x2b3c9d6f4105]
[n12-04:07131] [ 3] /usr/lib64/libstdc++.so.6(_ZN9__gnu_cxx27__verbose_terminate_handlerEv+0x12d) [0x2b3c9cdb6a5d]
[n12-04:07131] [ 4] /usr/lib64/libstdc++.so.6(+0xbcbe6) [0x2b3c9cdb4be6]
[n12-04:07131] [ 5] /usr/lib64/libstdc++.so.6(+0xbcc13) [0x2b3c9cdb4c13]
[n12-04:07131] [ 6] /usr/lib64/libstdc++.so.6(+0xbcd0e) [0x2b3c9cdb4d0e]
[n12-04:07131] [ 7] SU2_CFD(_ZN9CSysSolve14modGramSchmidtEiRSt6vectorIS0_IdSaIdEESaIS2_EERS0_I10CSysVectorSaIS6_EE+0x25e) [0x8b389e]
[n12-04:07131] [ 8] SU2_CFD(_ZN9CSysSolve6FGMRESERK10CSysVectorRS0_R20CMatrixVectorProductR15CPreconditionerdmb+0x82d) [0x8b536d]
[n12-04:07131] [ 9] SU2_CFD(_ZN12CEulerSolver23ImplicitEuler_IterationEP9CGeometryPP7CSolverP7CConfig+0x63c) [0x6918dc]
[n12-04:07131] [10] SU2_CFD(_ZN21CMultiGridIntegration15MultiGrid_CycleEPPP9CGeometryPPPP7CSolverPPPPP9CNumericsPP7CConfigtttmt+0x359) [0x4d7819]
[n12-04:07131] [11] SU2_CFD(_ZN21CMultiGridIntegration19MultiGrid_IterationEPPP9CGeometryPPPP7CSolverPPPPP9CNumericsPP7CConfigtmt+0x371) [0x4d8801]
[n12-04:07131] [12] SU2_CFD(_Z17MeanFlowIterationP7COutputPPP12CIntegrationPPP9CGeometryPPPP7CSolverPPPPP9CNumericsPP7CConfigPP16CSurfaceMovementPP19CVolumetricMovementPPP15CFreeFormDefBox+0x67a) [0x4ee4fa]
[n12-04:07131] [13] SU2_CFD(main+0xb52) [0x735072]
[n12-04:07131] [14] /lib64/libc.so.6(__libc_start_main+0xfd) [0x2b3c9d6ded1d]
[n12-04:07131] [15] SU2_CFD() [0x47ce69]
[n12-04:07131] *** End of error message ***

[...]

------------------------ Physical case definition -----------------------
Input mesh file name: naca0015_rotated.su2

-------------------------- Output information ---------------------------
The output file format is Tecplot ASCII (.dat).
Flow variables file name: flow.

------------------- Config file boundary information --------------------
Far-field boundary marker(s): farfield.
Symmetry plane boundary marker(s): symmetry.
Constant heat flux wall boundary marker(s): wing, flatplate.

---------------------- Read grid file information -----------------------
Three dimensional problem.
727478 interior elements including halo cells. 
727478 hexahedra.
677150 points, and 156763 ghost points.
Identify vertices.

------------------------- Solution Postprocessing -----------------------
[...]

------------------------- Exit Success (SU2_SOL) ------------------------
Attached Images
File Type: jpg residulas.jpg (56.4 KB, 25 views)
File Type: jpg grid.jpg (96.8 KB, 28 views)
Zen is offline   Reply With Quote

Old   September 21, 2014, 22:20
Default
  #2
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Francisco Palacios
Join Date: Jan 2013
Location: Long Beach, CA
Posts: 404
Rep Power: 12
fpalacios is on a distinguished road
Quote:
Originally Posted by Zen View Post
Hello Everybody,

I am trying to simulate a naca 0015 wing attached perpendicularly to a flat plate.
The Mach number is ~0.1 and I am using the compressible solver.
My stopping criterion is based on the reduction of the residual of 4 orders of magnitude.
I am using a coarse mesh with 7*10^5 cells.

However, I have problems with the convergence.
Is it because I am using the compressible solver ?( I tried to use the incompressible one and it still doesn't converge).
Or is there a problem with the settings of my configuration file?

Attached are a plot of the residuals, an image of the mesh and a file containing the info specified in the configuration file and the error I get after ca. 30000 iterations.

Any help is appreciated.

Thanks,

Z

Code:
------------------------ Physical case definition -----------------------
Compressible RANS equations.
Turbulence model: Spalart Allmaras
Mach number: 0.098.
Angle of attack (AoA): 6 deg, and angle of sideslip (AoS): 0 deg.
Reynolds number: 762000.
No restart solution, use the values at infinity (freestream).
The reference length/area will be computed using y(2D) or z(3D) projection.
The reference length (moment computation) is 0.34.
Reference origin (moment computation) is (0.25, 0, 0).
Surface(s) where the force coefficients are evaluated: wing.
Surface(s) plotted in the output file: wing.
Input mesh file name: naca0015_rotated.su2

---------------------- Space numerical integration ----------------------
Roe solver for the flow inviscid terms.
Second order integration with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 10. 
The reference element size is: 0.34. 
Scalar upwind solver (first order) for the turbulence model.
First order integration.
Average of gradients with correction (viscous flow terms).
Piecewise constant integration of the flow source terms.
Average of gradients with correction (viscous turbulence terms).
Piecewise constant integration of the turbulence model source terms.
Gradient computation using Green-Gauss theorem.

---------------------- Time numerical integration -----------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
CFL ramp definition. factor: 1.1, every 1000 iterations, with a limit of 10.
Courant-Friedrichs-Lewy number:        1
Euler implicit time integration for the turbulence model.

------------------------- Convergence criteria --------------------------
Maximum number of iterations: 999999.
Reduce the density residual 5 orders of magnitude.
The minimum bound for the density residual is 10^(-10).
Start convergence criteria at iteration 10.

-------------------------- Output information ---------------------------
Writing a flow solution every 250 iterations.
Writing the convergence history every 1 iterations.
The output file format is Tecplot ASCII (.dat).
Convergence history file name: history.
Surface flow coefficients file name: surface_flow.
Flow variables file name: flow.
Restart flow file name: restart_flow.dat.

------------------- Config file boundary information --------------------
Far-field boundary marker(s): farfield.
Symmetry plane boundary marker(s): symmetry.
Constant heat flux wall boundary marker(s): wing, flatplate.

---------------------- Read grid file information -----------------------
Three dimensional problem.
727478 interior elements including halo cells. 
[n12-04:07091] 47 more processes have sent help message help-mpi-btl-base.txt / btl:no-nics
[n12-04:07091] Set MCA parameter "orte_base_help_aggregate" to 0 to see all help / error messages
727478 hexahedra.
677150 points, and 156763 ghost points.

------------------------- Geometry Preprocessing ------------------------
Setting point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
Identifying edges and vertices.
Computing centers of gravity.
Setting the control volume structure.
Volume of the computational grid: 370.
Searching for the closest normal neighbors to the surfaces.
Compute the surface curvature.
Max K: 0. Mean K: 0. Standard deviation K: 0.

------------------------- Solver Preprocessing --------------------------
Computing wall distances.
Area projection in the z-plane = 0.995.
Viscous flow: Computing pressure using the ideal gas law
based on the free-stream temperature and a density computed
from the Reynolds number.
Note: Negative pressure, temperature or density is not allowed!
Force coefficients computed using free-stream values.
-- Input conditions:
Specific gas constant: 287.058 N.m/kg.K.
Free-stream pressure: 99463.3 Pa.
Free-stream temperature: 288.15 K.
Free-stream density: 1.20247 kg/m^3.
Free-stream velocity: (33.1664, 0, 3.48593) m/s. Magnitude: 33.3491 m/s.
Free-stream total energy per unit mass: 207345 m^2/s^2.
Free-stream viscosity: 1.7893e-05 N.s/m^2.
Free-stream turb. kinetic energy per unit mass: 4.17061 m^2/s^2.
Free-stream specific dissipation: 28028 1/s.
-- Reference values:
Reference specific gas constant: 1 N.m/kg.K.
Reference pressure: 1 Pa.
Reference temperature: 1 K.
Reference density: 1 kg/m^3.
Reference velocity: 1 m/s.
Reference energy per unit mass: 1 m^2/s^2.
Reference viscosity: 1 N.s/m^2.
-- Resulting non-dimensional state:
Mach number (non-dim): 0.098
Reynolds number (non-dim): 762000. Re length: 0.34 m.
Specific gas constant (non-dim): 287.058
Free-stream temperature (non-dim): 288.15
Free-stream pressure (non-dim): 99463.3
Free-stream density (non-dim): 1.20247
Free-stream velocity (non-dim): (33.1664, 0, 3.48593). Magnitude: 33.3491
Free-stream total energy per unit mass (non-dim): 207345
Free-stream viscosity (non-dim): 1.7893e-05
Free-stream turb. kinetic energy (non-dim): 4.17061
Free-stream specific dissipation (non-dim): 28028

Initialize jacobian structure (Navier-Stokes). MG level: 0.
Initialize jacobian structure (SA model).

------------------------------ Begin Solver -----------------------------

 Maximum residual: -1.25842, located at point 41549.

 Iter    Time(s)      Res[Rho]       Res[nu]   CLift(Total)   CDrag(Total)
    0   1.590721     -3.210747     -5.593713       1.565292       1.150936
[...]
38618   1.908126     -7.419505     -6.272192       0.632451       0.035221
38619   1.908131     -7.419517     -6.272200       0.632451       0.035221
CSysSolve::modGramSchmidt: w[i+1] = NaN
CSysSolve::modGramSchmidt: w[i+1] = NaN
terminate called after throwing an instance of 'CSysSolve::modGramSchmidt: w[i+1] = NaN
terminate called after throwing an instance of 'int'
CSysSolve::modGramSchmidt: w[i+1] = NaN
CSysSolve::modGramSchmidt: w[i+1] = NaN
CSysSolve::modGramSchmidt: w[i+1] = NaN
CSysSolve::modGramSchmidt: w[i+1] = NaN
int'
[n12-04:07125] *** Process received signal ***
[n12-04:07125] Signal: Aborted (6)
[n12-04:07125] Signal code:  (-6)
CSysSolve::modGramSchmidt: w[i+1] = NaN
terminate called after throwing an instance of 'int'
[...]
[n12-04:07137] *** Process received signal ***
[n12-04:07137] Signal: Aborted (6)
[n12-04:07137] Signal code:  (-6)
[n12-04:07114] *** Process received signal ***
[n12-04:07114] Signal: Aborted (6)
[n12-04:07114] Signal code:  (-6)
[n12-04:07131] [ 0] /lib64/libpthread.so.0(+0xf710) [0x2b3c9d4af710]
[n12-04:07131] [ 1] /lib64/libc.so.6(gsignal+0x35) [0x2b3c9d6f2925]
[n12-04:07131] [ 2] /lib64/libc.so.6(abort+0x175) [0x2b3c9d6f4105]
[n12-04:07131] [ 3] /usr/lib64/libstdc++.so.6(_ZN9__gnu_cxx27__verbose_terminate_handlerEv+0x12d) [0x2b3c9cdb6a5d]
[n12-04:07131] [ 4] /usr/lib64/libstdc++.so.6(+0xbcbe6) [0x2b3c9cdb4be6]
[n12-04:07131] [ 5] /usr/lib64/libstdc++.so.6(+0xbcc13) [0x2b3c9cdb4c13]
[n12-04:07131] [ 6] /usr/lib64/libstdc++.so.6(+0xbcd0e) [0x2b3c9cdb4d0e]
[n12-04:07131] [ 7] SU2_CFD(_ZN9CSysSolve14modGramSchmidtEiRSt6vectorIS0_IdSaIdEESaIS2_EERS0_I10CSysVectorSaIS6_EE+0x25e) [0x8b389e]
[n12-04:07131] [ 8] SU2_CFD(_ZN9CSysSolve6FGMRESERK10CSysVectorRS0_R20CMatrixVectorProductR15CPreconditionerdmb+0x82d) [0x8b536d]
[n12-04:07131] [ 9] SU2_CFD(_ZN12CEulerSolver23ImplicitEuler_IterationEP9CGeometryPP7CSolverP7CConfig+0x63c) [0x6918dc]
[n12-04:07131] [10] SU2_CFD(_ZN21CMultiGridIntegration15MultiGrid_CycleEPPP9CGeometryPPPP7CSolverPPPPP9CNumericsPP7CConfigtttmt+0x359) [0x4d7819]
[n12-04:07131] [11] SU2_CFD(_ZN21CMultiGridIntegration19MultiGrid_IterationEPPP9CGeometryPPPP7CSolverPPPPP9CNumericsPP7CConfigtmt+0x371) [0x4d8801]
[n12-04:07131] [12] SU2_CFD(_Z17MeanFlowIterationP7COutputPPP12CIntegrationPPP9CGeometryPPPP7CSolverPPPPP9CNumericsPP7CConfigPP16CSurfaceMovementPP19CVolumetricMovementPPP15CFreeFormDefBox+0x67a) [0x4ee4fa]
[n12-04:07131] [13] SU2_CFD(main+0xb52) [0x735072]
[n12-04:07131] [14] /lib64/libc.so.6(__libc_start_main+0xfd) [0x2b3c9d6ded1d]
[n12-04:07131] [15] SU2_CFD() [0x47ce69]
[n12-04:07131] *** End of error message ***

[...]

------------------------ Physical case definition -----------------------
Input mesh file name: naca0015_rotated.su2

-------------------------- Output information ---------------------------
The output file format is Tecplot ASCII (.dat).
Flow variables file name: flow.

------------------- Config file boundary information --------------------
Far-field boundary marker(s): farfield.
Symmetry plane boundary marker(s): symmetry.
Constant heat flux wall boundary marker(s): wing, flatplate.

---------------------- Read grid file information -----------------------
Three dimensional problem.
727478 interior elements including halo cells. 
727478 hexahedra.
677150 points, and 156763 ghost points.
Identify vertices.

------------------------- Solution Postprocessing -----------------------
[...]

------------------------- Exit Success (SU2_SOL) ------------------------
Could you please run the simulation at a fix CFL number (let's say 1.0 - without ramping- ).

Visualize the limiter and residuals
WRT_RESIDUALS= YES
WRT_LIMITERS= YES
could be also useful to identify the problem.

And do not forget to play with the slope-limiting coefficient.

Cheers,
Francisco
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Old   September 22, 2014, 06:20
Default
  #3
Zen
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Zeno
Join Date: Sep 2013
Location: Delft, The Netherlands
Posts: 63
Rep Power: 9
Zen is on a distinguished road
Dear Francisco,

Thank you for your reply. It was definitely the value of the slope limiting coefficient.
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Old   October 14, 2014, 13:28
Default
  #4
Zen
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Zeno
Join Date: Sep 2013
Location: Delft, The Netherlands
Posts: 63
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For the same test case, I wanted to see if I get better results when Roe-Turkel preconditioning is activated.

I therefore set:

Code:
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
%                              TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= TURKEL_PREC
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
SPATIAL_ORDER_FLOW= 2ND_ORDER_LIMITER
But I get non physical points after less than 50 iterations.

If I change to a first order spatial integration

Code:
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
%                              TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= TURKEL_PREC
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
SPATIAL_ORDER_FLOW= 1ST_ORDER
The simulation does not converge since the residual keeps being constant.


Any hint here?

Thank you,


Zeno
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Old   May 2, 2019, 00:47
Default
  #5
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Muhammad Hilmi Al Fatih
Join Date: Apr 2019
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Hey Zeno!


I recently tried to run the low mach number case using a compressible solver too. I am a bit frustrated since it did take very long time to converge. I wonder if you could give any further results on your trial on that problem? Did you finally succeed to get a converged solution using turkel-preconditioning scheme?

Also, could you please further elaborate how did you play with the slope limiting coefficient and how was the effect of it?


Looking forward to your answer.


Cheers,
Hilmi
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Old   May 2, 2019, 06:02
Default
  #6
Zen
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Zeno
Join Date: Sep 2013
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HI Muhammad,

please note that this is a 5-year old thread and SU2 has changed a lot in this time.
I haven't been running incompressible simulations in a while so I don't know how SU2 is handling these cases at the moment. By looking at the config files of a simulation similar to the one above, it seemed that I settled for the following options (which may be specified with another syntax in the current version of SU2):


Code:
% Reference element length for computing the slope and sharp edges limiters.
REF_ELEM_LENGTH= 0.1
%
% Coefficient for the limiter
LIMITER_COEFF= 0.1
%

% Linear solver for implicit formulations (BCGSTAB, FGMRES)
LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS)
LINEAR_SOLVER_PREC= LU_SGS
%
% Minimum error of the linear solver for implicit formulations
LINEAR_SOLVER_ERROR= 1E-4
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 5
%

% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
% TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= ROE
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_FLOW= 2ND_ORDER_LIMITER
%
% Slope limiter (VENKATAKRISHNAN, MINMOD)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN

Have a look at Venkatakrishnan's paper if you want to understand how to specify limiters.



Best,

Zeno
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Old   May 3, 2019, 05:51
Default
  #7
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Muhammad Hilmi Al Fatih
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Dea Zeno,


Thank you for your prompt reply. It is really helpful.


Regards,
Hilmi
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compressible, convergence criteria, incompressible, junction flows

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