- **SU2**
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- - **multi-species plasma test case**
(*http://www.cfd-online.com/Forums/su2/124898-multi-species-plasma-test-case.html*)

multi-species plasma test caseI've just installed the newest 2.0.8 from github.
I'm trying to run the multi-species react-argon case, and am getting a lot of errors. I'm using the config file from the newest release. see below: -------------------------------------------------------------------------------------- SU2_CFD plasma_argon_3D.cfg WARNING: unrecognized option in the config. file: MIXTURE_MOLAR_MASS. WARNING: unrecognized option in the config. file: BLOCK_DIAGONAL_JACOBIAN. WARNING: unrecognized option in the config. file: MG_RESTART_CYCLE. WARNING: unrecognized option in the config. file: NUMBER_OF_SPECIES_IN_PLASMA. WARNING: unrecognized option in the config. file: NUMBER_OF_CHEMICAL_REACTIONS. WARNING: unrecognized option in the config. file: PARTICLE_MASS. WARNING: unrecognized option in the config. file: MAGNETIC_DIPOLE. WARNING: unrecognized option in the config. file: SOUR_NUM_METHOD_ELEC. WARNING: unrecognized option in the config. file: VISC_NUM_METHOD_ELEC. WARNING: unrecognized option in the config. file: CYCLE_ADAPT. WARNING: unrecognized option in the config. file: HORIZONTAL_PLANE_POSITION. WARNING: unrecognized option in the config. file: HORIZONTAL_PLANE_MARKER. WARNING: unrecognized option in the config. file: ONESHOT_CAUCHY_EPS. WARNING: No species CFL numbers specified for plasma multi-timestepping, using mean flow CFL parameters WARNING: No species CFL ramp iteration specified for plasma multi-timestepping, using mean flow CFL parameters WARNING: No maximum CFL specified for plasma multi-timestepping, using mean flow CFL parameters ------------------------------------------------------------------------- | _____ _ _ ___ | | / ____| | | | | |__ \ Web: su2.stanford.edu | | | (___ | | | | ) | Twitter: @su2code | | \___ \ | | | | / / Forum: www.cfd-online.com/Forums/su2/ | | ____) | | |__| | / /_ | | |_____/ \____/ |____| Suite (Computational Fluid Dynamic Code) | | Release 2.0.8 | ------------------------------------------------------------------------- | Stanford University Unstructured (SU2). | | Copyright (C) 2012-2013 Aerospace Design Laboratory (ADL). | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License (version 2.1) for more details. | ------------------------------------------------------------------------- ------------------------ Physical case definition ----------------------- Plasma equations (with viscosity). Using 3 species Argon gas model. Mach number: 4.6. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). The reference length/area (force coefficient) is 1. The reference length (moment computation) is 1. Reference origin (moment computation) is (0.25, 0, 0). Surface(s) where the force coefficients are evaluated: BulletHead. Surface(s) where the objective function is evaluated: Surface(s) plotted in the output file: BulletHead. Surface(s) affected by the design variables: Input mesh file name: mesh_plasma_argon_3D.su2 ---------------------- Space numerical integration ---------------------- 1st order Roe solver for the plasma inviscid terms. Average of gradients (1st order) for computation of viscous flow terms. Piecewise constant integration of the plasma source terms. Gradient computation using Green-Gauss theorem. ---------------------- Time numerical integration ----------------------- Local time stepping (steady state simulation). Euler implicit method for the plasma equations. CFL ramp definition. factor: 1.1, every 100 iterations, with a limit of 8. Courant-Friedrichs-Lewy number: 0.5 ------------------------- Convergence criteria -------------------------- Maximum number of iterations: 5. Reduce the density residual 6 orders of magnitude. The minimum bound for the density residual is 10^(-22). 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 variables file name: solution. Restart flow file name: restart.dat. ------------------- Config file boundary information -------------------- Far-field boundary marker(s): Inlet, Exit. Symmetry plane boundary marker(s): Sidewall1, Sidewall2. Constant heat flux wall boundary marker(s): BulletHead. ---------------- Flow & Non-dimensionalization information --------------- Viscous flow: Computing pressure using the ideal gas law based on the freestream temperature and a density computed from the Reynolds number. --Input conditions: Grid conversion factor to meters: 1 Ratio of specific heats: 1.66667 Specific gas constant (J/(kg.K)): 208 Freestream pressure (N/m^2): 0 Freestream temperature (K): 810 Freestream density (kg/m^3): 0 Freestream velocity (m/s): (2437.57,0,0) Freestream velocity magnitude (m/s):2437.57 Freestream energy (kg.m/s^2): -nan Freestream viscosity (N.s/m^2): 3.66516e-05 --Reference values: Reference pressure (N/m^2): 1 Reference temperature (K): 1 Reference energy (kg.m/s^2): -nan Reference density (kg/m^3): 1 Reference velocity (m/s): 1 Reference viscosity (N.s/m^2): 1 --Resulting non-dimensional state: Mach number (non-dimensional): 4.6 Reynolds number (non-dimensional): 0 Reynolds length (m): 1 Froude number (non-dimensional): 778.388 Lenght of the baseline wave (non-dimensional): 3.8069e+06 Negative pressure, temperature or density is not allowed! Specific gas constant (non-dimensional): 208 Freestream temperature (non-dimensional): 810 Freestream pressure (non-dimensional): 0 Freestream density (non-dimensional): 0 Freestream velocity (non-dimensional): (2437.57,0,0) Freestream velocity magnitude (non-dimensional): 2437.57 Freestream energy (non-dimensional): -nan Freestream viscosity (non-dimensional): 3.66516e-05 Force coefficients computed using freestream values. ---------------------- Read grid file information ----------------------- Three dimensional problem. 46327 interior elements. 31600 tetrahedra. 13104 hexahedra. 1623 pyramids. 22557 points. 6 surface markers. 315 boundary elements in index 0 (Marker = BulletHead). 238 boundary elements in index 1 (Marker = Cylinder). The configuration file doesn't have any definition for marker Cylinder!! |

Hi Tom,
The reacting-gas solver is currently undergoing a complete overhaul and, unfortunately, the test case in the repository and in the user guide is out-of-date. I apologize for the inconvenience, I've temporarily removed it from both locations until I can appropriately document the changes and set up a proper test-case for the community. Thanks for bringing it to my attention. The new implementation will be finished in a month or two and I encourage you to stay tuned for updates. Thanks. Regards, Sean |

I actually got the first part of it to run by checking and re-checking the input items and config_structure.cpp and taking out the wrong and discontinued items.
I started it euler, and it runs and gives me a solution that looks proper. However, no matter what I try, I get nan's when re-starting. Whether I run 25 iterations and restart or whether I run 15,000 and restart. |

Hi Tom,
I'm glad to hear that you've seen some life in the reacting-gas solver. There are likely settings in the configuration file that are referencing defunct and obsolete subroutines within the old reacting gas solver that are contributing to your difficulties. The old code will be removed for the next interim release. This may also be contributing to your restart-file issues. Francisco and I sent you a mesh and configuration file the other day, I would encourage you to try running that case as a starting point. Be sure you are referencing the TNE2_EULER solver (NOT the PLASMA_EULER solver), and set the GAS_MODEL=N2. Again, I want to stress that the reacting-gas solver is not supported at this time. Many of the settings are not well-documented. If you continue to have difficulty, please send me an email and I will do my best to assist. Thanks, Sean |

Yes, I planned on continuing with that tne case you sent earlier... thanks for that.
I'll hold off on the plasma case for now. |

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