Console Output

Skipping 473 KB.. Full Log
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

------------------- Numerics Preprocessing ( Zone 0 ) -------------------

----------------- Integration Preprocessing ( Zone 0 ) ------------------

------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  2.6492e-01|   -0.348385|    1.966931|    1.613249|    5.120721|   -1.717816|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  2.6888e-01|   -0.442403|    2.014793|    1.899130|    5.021091|   -1.860916|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  2.7132e-01|   -0.571089|    1.888985|    2.017639|    4.890427|   -1.771257|

----------------------------- Solver Exit -------------------------------

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.571089|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticSimple_Iterative_SM.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file                           |surface_flow_aeroelasticSimple_Iterative_SM.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary                     |flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface             |surface_flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


Running PostAnalysis ...... su2

Running PreAnalysis ...... su2
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 3.109685e+09, tgt = 3.109685e+09, diff = 9.347420e-01
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 3.021395e+09, tgt = 3.021395e+09, diff = 7.515732e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 3.789177e+07, tgt = 3.789177e+07, diff = 0.000000e+00
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 4 (total = 4)
	TransferName = Skin_Bottom
	Number of Elements = 4 (total = 8)
	TransferName = Skin_Tip
	Number of Elements = 2 (total = 10)

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file


Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 12
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 12
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 12
	Loading displacements for Subcase = 1
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../tetgen/tetgen_0.su2

---------------- Grid deformation parameters ( Zone 0 )  ----------------
Grid deformation using a linear elasticity method.


-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aeroelasticSimple_Iterative_SM.su2. 
Cell stiffness scaled by distance to nearest solid surface.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+
Three dimensional problem.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 tetrahedra.

----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identify edges and vertices.
Setting the bound control volume structure.
Volume of the computational grid: 63999.5.
  Info: Ignoring the following volume output fields/groups:
  SOLUTION
Volume output fields: COORDINATES
  Info: Ignoring the following screen output fields:
  RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME
  Info: Ignoring the following history output groups:
  RMS_RES, AERO_COEFF
History output group(s): ITER, TIME_DOMAIN, WALL_TIME
Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive.
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.

--------------------- Surface grid deformation (ZONE 0) -----------------
Performing the deformation of the surface grid.
Updating the surface coordinates from the input file.

------------------- Volumetric grid deformation (ZONE 0) ----------------
Performing the deformation of the volumetric grid.

WARNING: Convexity is not checked for 3D elements (issue #1171).


----------------------- Write deformed grid files -----------------------
|SU2 mesh                           |aeroelasticSimple_Iterative_SM.su2 |
|CSV file                           |surface_deformed.csv               |
|Tecplot binary                     |volume_deformed.szplt              |
|Tecplot binary surface             |surface_deformed.szplt             |
Adding any FFD information to the SU2 file.

------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

Completed in 0.754444 seconds on 1 core.

------------------------- Exit Success (SU2_DEF) ------------------------


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_3.

Surface(s) plotted in the output file: BC_3.
Surface(s) affected by the design variables: BC_3.
Input mesh file name: ../tetgen/tetgen_0.su2

--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1. 
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.

--------------- Time Numerical Integration  ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------ Convergence Criteria  ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 3.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_SM.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+

-------------------- Output Preprocessing ( Zone 0 ) --------------------

WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)

Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 63999.5.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 27.1257. Mean K: 0.0598259. Standard deviation K: 0.945506.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        12.6541|        83.7062|
|     CV Face Area Aspect Ratio|        1.45416|        3253.37|
|           CV Sub-Volume Ratio|              1|    2.23538e+32|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      5348|    1/1.00|        10|
|         1|       988|    1/5.41|   8.54305|
|         2|       177|    1/5.58|   7.22398|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 7.57417 m^2.
Area projection in the x-plane = 0.549259 m^2, y-plane = 0.226217 m^2, z-plane = 3.60855 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.37568 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.09713e-18 m, z-direction = -0.0342487 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is a single plane.
Computing wall distances.

-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

------------------- Numerics Preprocessing ( Zone 0 ) -------------------

----------------- Integration Preprocessing ( Zone 0 ) ------------------

------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  2.0971e-01|   -0.348385|    1.966931|    1.613249|    5.120721|   -1.717816|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  2.0897e-01|   -0.442403|    2.014793|    1.899130|    5.021091|   -1.860916|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  2.0921e-01|   -0.571089|    1.888985|    2.017639|    4.890427|   -1.771257|

----------------------------- Solver Exit -------------------------------

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.571089|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticSimple_Iterative_SM.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file                           |surface_flow_aeroelasticSimple_Iterative_SM.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary                     |flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface             |surface_flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


Running PostAnalysis ...... su2

Running PreAnalysis ...... su2
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 3.109685e+09, tgt = 3.109685e+09, diff = 9.347420e-01
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 3.021395e+09, tgt = 3.021395e+09, diff = 7.515732e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 3.789177e+07, tgt = 3.789177e+07, diff = 0.000000e+00
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 4 (total = 4)
	TransferName = Skin_Bottom
	Number of Elements = 4 (total = 8)
	TransferName = Skin_Tip
	Number of Elements = 2 (total = 10)

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file


Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 12
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 12
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 12
	Loading displacements for Subcase = 1
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../tetgen/tetgen_0.su2

---------------- Grid deformation parameters ( Zone 0 )  ----------------
Grid deformation using a linear elasticity method.


-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aeroelasticSimple_Iterative_SM.su2. 
Cell stiffness scaled by distance to nearest solid surface.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+
Three dimensional problem.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 tetrahedra.

----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identify edges and vertices.
Setting the bound control volume structure.
Volume of the computational grid: 63999.5.
  Info: Ignoring the following volume output fields/groups:
  SOLUTION
Volume output fields: COORDINATES
  Info: Ignoring the following screen output fields:
  RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME
  Info: Ignoring the following history output groups:
  RMS_RES, AERO_COEFF
History output group(s): ITER, TIME_DOMAIN, WALL_TIME
Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive.
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.

--------------------- Surface grid deformation (ZONE 0) -----------------
Performing the deformation of the surface grid.
Updating the surface coordinates from the input file.

------------------- Volumetric grid deformation (ZONE 0) ----------------
Performing the deformation of the volumetric grid.

WARNING: Convexity is not checked for 3D elements (issue #1171).


----------------------- Write deformed grid files -----------------------
|SU2 mesh                           |aeroelasticSimple_Iterative_SM.su2 |
|CSV file                           |surface_deformed.csv               |
|Tecplot binary                     |volume_deformed.szplt              |
|Tecplot binary surface             |surface_deformed.szplt             |
Adding any FFD information to the SU2 file.

------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

Completed in 0.616598 seconds on 1 core.

------------------------- Exit Success (SU2_DEF) ------------------------


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_3.

Surface(s) plotted in the output file: BC_3.
Surface(s) affected by the design variables: BC_3.
Input mesh file name: ../tetgen/tetgen_0.su2

--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1. 
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.

--------------- Time Numerical Integration  ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------ Convergence Criteria  ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 3.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_SM.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+

-------------------- Output Preprocessing ( Zone 0 ) --------------------

WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)

Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 63999.5.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 27.1257. Mean K: 0.0598259. Standard deviation K: 0.945506.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        12.6541|        83.7062|
|     CV Face Area Aspect Ratio|        1.45416|        3253.37|
|           CV Sub-Volume Ratio|              1|    2.23538e+32|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      5348|    1/1.00|        10|
|         1|       988|    1/5.41|   8.54305|
|         2|       177|    1/5.58|   7.22398|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 7.57417 m^2.
Area projection in the x-plane = 0.549259 m^2, y-plane = 0.226217 m^2, z-plane = 3.60855 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.37568 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.09713e-18 m, z-direction = -0.0342487 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is a single plane.
Computing wall distances.

-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

------------------- Numerics Preprocessing ( Zone 0 ) -------------------

----------------- Integration Preprocessing ( Zone 0 ) ------------------

------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  2.7632e-01|   -0.348385|    1.966931|    1.613249|    5.120721|   -1.717816|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  2.7534e-01|   -0.442403|    2.014793|    1.899130|    5.021091|   -1.860916|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  2.7739e-01|   -0.571089|    1.888985|    2.017639|    4.890427|   -1.771257|

----------------------------- Solver Exit -------------------------------

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.571089|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticSimple_Iterative_SM.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file                           |surface_flow_aeroelasticSimple_Iterative_SM.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary                     |flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface             |surface_flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


Running PostAnalysis ...... su2
Cl =  -0.371716
Cd =  0.20986

real	0m22.386s
user	0m14.831s
sys	0m3.336s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_SU2_and_Mystran.py passed (as expected)
=================================================

mystran: /home/jenkins/util/mystran/MYSTRAN/Binaries/mystran
flowCart: /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//flowCart

=================================================
+ echo 'aeroelasticSimple_Iterative_Cart3D_and_Mystran.py test;'
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
aeroelasticSimple_Iterative_Cart3D_and_Mystran.py test;
+ python -u aeroelasticSimple_Iterative_Cart3D_and_Mystran.py -outLevel=0
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Skin, index = 1
	Name = Rib_Root, index = 2
 Body size = 4.649612
 Tessellating body 1 with  MaxEdge = 0.232481  Sag = 0.232481  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 9  > autoInputs.out
 Executing: ./aero.csh > aero.out
Cl =  0.11601106
Cd =  0.059861711
Mapping Csys attributes ................
	Number of unique Csys attributes = 0

Getting FEA coordinate systems.......
	Number of coordinate systems - 0
	No coordinate systems found - defaulting to global
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = Rib_Root, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 1
	Name = Skin, index = 1
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 3
	Name = Skin_Top, index = 1
	Name = Skin_Bottom, index = 2
	Name = Skin_Tip, index = 3
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Skin, index = 1
	Name = Rib_Root, index = 2
Creating FEA BEM
	Getting quads for BEM!
	Mesh for body = 0
	Number of nodal coordinates = 145
	Number of elements = 160
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 34
	Elemental Quad4 = 126

Getting FEA materials.......
	Number of materials - 1
	Material name - Madeupium
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 2
	Property name - Rib_Root
	Property name - Skin
	Done getting FEA properties

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - edgeConstraint
	No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement"
	Done getting FEA constraints
Support tuple is NULL - No supports applied

Getting FEA loads.......
	Number of loads - 1
	Load name - pressureAero
	No "groupName" specified for Load tuple pressureAero, going to use load name
	Done getting FEA loads

Analysis tuple is NULL
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 2.207070e+04, tgt = 2.207070e+04, diff = 4.705435e-03
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 2.166463e+04, tgt = 2.166463e+04, diff = 1.856329e-03
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 3.226195e+02, tgt = 3.226195e+02, diff = 1.364754e-09
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 63 (total = 63)
	TransferName = Skin_Bottom
	Number of Elements = 63 (total = 126)
	TransferName = Skin_Tip
	Number of Elements = 12 (total = 138)

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file


Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 145
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 145
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 145
	Loading displacements for Subcase = 1
 Executing: ./aero.csh > aero.out
Cl =  0.11271792
Cd =  0.061811274
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 2.205109e+04, tgt = 2.205109e+04, diff = 1.031963e-03
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 2.163938e+04, tgt = 2.163937e+04, diff = 1.369227e-03
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 3.221580e+02, tgt = 3.221580e+02, diff = 2.901515e-09
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 63 (total = 63)
	TransferName = Skin_Bottom
	Number of Elements = 63 (total = 126)
	TransferName = Skin_Tip
	Number of Elements = 12 (total = 138)

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file


Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 145
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 145
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 145
	Loading displacements for Subcase = 1
 Executing: ./aero.csh > aero.out
Cl =  0.11724219
Cd =  0.062069478
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 2.204624e+04, tgt = 2.204624e+04, diff = 4.195111e-04
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 2.164591e+04, tgt = 2.164591e+04, diff = 2.907462e-03
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 3.219266e+02, tgt = 3.219266e+02, diff = 6.452808e-09
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 63 (total = 63)
	TransferName = Skin_Bottom
	Number of Elements = 63 (total = 126)
	TransferName = Skin_Tip
	Number of Elements = 12 (total = 138)

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file


Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 145
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 145
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 145
	Loading displacements for Subcase = 1
 Executing: ./aero.csh > aero.out
Cl =  0.11578184
Cd =  0.060809452

real	2m34.853s
user	4m56.282s
sys	0m5.111s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_Cart3D_and_Mystran.py passed (as expected)
=================================================


*************************************************
*************************************************

=================================================
Did not run examples for:

Astros
=================================================

All tests pass!

++ cd /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/legacy/examples/regressionTest
++ ./execute_PyTestRegression.sh AEROELASTIC

=================================================
Legacy Using python : /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP_venv/bin/python
=================================================

Running.... AEROELASTIC PyTests

=================================================
+ rm -rf aeroelasticSimple_Pressure_SU2_and_Mystran
+ echo 'aeroelasticSimple_Pressure_SU2_and_Mystran.py test;'
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
aeroelasticSimple_Pressure_SU2_and_Mystran.py test;
+ python -u aeroelasticSimple_Pressure_SU2_and_Mystran.py -verbosity=0 -workDir=runDirectory -noPlotData
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt

Running PreAnalysis ...... tetgen
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Farfield, index = 1
	Name = SymmPlane, index = 2
	Name = Skin, index = 3
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 0
Getting surface mesh for body 1 (of 1)

Running PostAnalysis ...... tetgen
Body 1 (of 1)
Number of nodes    = 12449
Number of elements = 24894
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 24894
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 12449
Total number of elements = 24894

Running PreAnalysis ...... tetgen
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Farfield, index = 1
	Name = SymmPlane, index = 2
	Name = Skin, index = 3
Number of surface nodes - 12449
Number of surface elements - 24894
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000QT1.00e-16
Done meshing using TetGen!
No project name ("Proj_Name") provided - A volume mesh will not be written out

Running PostAnalysis ...... tetgen

Running PreAnalysis ...... su2

Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Farfield
	Boundary condition name - Skin
	Boundary condition name - SymmPlane
	Done getting CFD boundary conditions
Info: No recognized data transfer names found.
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_3.

Surface(s) plotted in the output file: BC_3.
Surface(s) affected by the design variables: BC_3.
Input mesh file name: ../runDirectory_AeroelasticSimple_Pressure_tetgen_tetgenAIM/tetgen_0.su2

--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1. 
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.

--------------- Time Numerical Integration  ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------ Convergence Criteria  ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticSimple_Pressure_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Pressure_SM.
Volume file name: flow_aeroelasticSimple_Pressure_SM.
Restart file name: restart_flow_aeroelasticSimple_Pressure_SM.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+

-------------------- Output Preprocessing ( Zone 0 ) --------------------

WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)

Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
22560 grid points.
98725 volume elements.
3 surface markers.
342 boundary elements in index 0 (Marker = BC_1).
12856 boundary elements in index 1 (Marker = BC_2).
11696 boundary elements in index 2 (Marker = BC_3).
98725 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 63999.5.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 1594.52. Mean K: 49.8216. Standard deviation K: 81.7526.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        14.2921|        84.8436|
|     CV Face Area Aspect Ratio|        1.65091|        10423.3|
|           CV Sub-Volume Ratio|              1|         267774|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     22560|    1/1.00|        10|
|         1|      4201|    1/5.37|   8.56569|
|         2|       997|    1/4.21|    7.9549|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 10.0438 m^2.
Area projection in the x-plane = 0.679139 m^2, y-plane = 0.327414 m^2, z-plane = 4.84583 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380458 m.
Min. coordinate in the x-direction = -0.000478065 m, y-direction = -2.86151e-18 m, z-direction = -0.0467319 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is a single plane.
Computing wall distances.

-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

------------------- Numerics Preprocessing ( Zone 0 ) -------------------

----------------- Integration Preprocessing ( Zone 0 ) ------------------

------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  9.6448e-01|   -1.523025|    0.609925|    0.080721|    3.946081|   -0.718239|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  9.6976e-01|   -1.339928|    1.151012|    0.965895|    4.131543|   -0.220381|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  9.9416e-01|   -1.396967|    1.128043|    1.048458|    4.059504|    2.124723|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  1.0029e+00|   -1.363292|    1.004045|    0.944956|    4.100976|  -17.543179|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.0173e+00|   -1.425272|    0.899661|    0.911531|    4.035349|   -9.050381|

----------------------------- Solver Exit -------------------------------

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.42527|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticSimple_Pressure_SM.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SM.dat).
|CSV file                           |surface_flow_aeroelasticSimple_Pressure_SM.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SM.dat).
|Tecplot binary                     |flow_aeroelasticSimple_Pressure_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SM.dat).
|Tecplot binary surface             |surface_flow_aeroelasticSimple_Pressure_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SM.dat).

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


Running PostAnalysis ...... su2

Executing dataTransfer ......
No variable name provided - defaulting to variable - Pressure
Mapping Csys attributes ................
	Number of unique Csys attributes = 0

Getting FEA coordinate systems.......
	Number of coordinate systems - 0
	No coordinate systems found - defaulting to global
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = Rib_Root, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 1
	Name = Skin, index = 1
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 3
	Name = Skin_Top, index = 1
	Name = Skin_Bottom, index = 2
	Name = Skin_Tip, index = 3
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Skin, index = 1
	Name = Rib_Root, index = 2
Creating FEA BEM
	Getting quads for BEM!
	Mesh for body = 0
	Number of nodal coordinates = 180
	Number of elements = 194
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 32
	Elemental Quad4 = 162

Getting FEA materials.......
	Number of materials - 1
	Material name - Madeupium
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 2
	Property name - Rib_Root
	Property name - Skin
	Done getting FEA properties

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - edgeConstraint
	No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement"
	Done getting FEA constraints
Support tuple is NULL - No supports applied

Getting FEA loads.......
	Number of loads - 1
	Load name - pressureAero
	No "groupName" specified for Load tuple pressureAero, going to use load name
	Done getting FEA loads

Analysis tuple is NULL
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SM.csv
	Number of variables = 13
	Number of data points = 5887
No variable name provided - defaulting to variable - Pressure
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SM.csv
	Number of variables = 13
	Number of data points = 5887
No variable name provided - defaulting to variable - Pressure
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SM.csv
	Number of variables = 13
	Number of data points = 5887

Running PreAnalysis ...... mystran
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 81 (total = 81)
	TransferName = Skin_Bottom
	Number of Elements = 81 (total = 162)
	TransferName = Skin_Tip
	Number of Elements = 16 (total = 178)

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file


Writing MYSTRAN instruction file....


Running Mystran......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL

Running PostAnalysis ...... mystran
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.aimName' is deprecated. Please use 'name'!
WARNING: 'capsAnalysis.getAnalysisInfo' is deprecated. Please use 'Analysis.info'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsBound.fillVertexSets' is deprecated. Please use 'None'!
WARNING: 'capsAnalysis.getAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsBound.executeTransfer' is deprecated. Please use 'None'!
WARNING: 'capsBound.getDestData' is deprecated. Please use 'vertexSet["name"].dataSet["variableName"].getData'!
WARNING: 'DataSet.getData' is deprecated. Please use 'DataSet.data'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	0m20.137s
user	0m20.192s
sys	0m1.915s
+ status=0
+ set +x

=================================================
Legacy CAPS verification (using pyCAPS) case aeroelasticSimple_Pressure_SU2_and_Mystran.py passed (as expected)
=================================================


=================================================
+ rm -rf aeroelasticSimple_Displacement_SU2_and_Mystran
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
+ echo 'aeroelasticSimple_Displacement_SU2_and_Mystran.py test;'
aeroelasticSimple_Displacement_SU2_and_Mystran.py test;
+ python -u aeroelasticSimple_Displacement_SU2_and_Mystran.py -verbosity=0 -workDir=runDirectory -noPlotData
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt

Running PreAnalysis ...... tetgen
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Farfield, index = 1
	Name = SymmPlane, index = 2
	Name = Skin, index = 3
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 0
Getting surface mesh for body 1 (of 1)

Running PostAnalysis ...... tetgen
Body 1 (of 1)
Number of nodes    = 12449
Number of elements = 24894
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 24894
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 12449
Total number of elements = 24894

Running PreAnalysis ...... tetgen
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Farfield, index = 1
	Name = SymmPlane, index = 2
	Name = Skin, index = 3
Number of surface nodes - 12449
Number of surface elements - 24894
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000QT1.00e-16
Done meshing using TetGen!
No project name ("Proj_Name") provided - A volume mesh will not be written out

Running PostAnalysis ...... tetgen

Running PreAnalysis ...... mystran
Mapping Csys attributes ................
	Number of unique Csys attributes = 0

Getting FEA coordinate systems.......
	Number of coordinate systems - 0
	No coordinate systems found - defaulting to global
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = Rib_Root, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 1
	Name = Skin, index = 1
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 3
	Name = Skin_Top, index = 1
	Name = Skin_Bottom, index = 2
	Name = Skin_Tip, index = 3
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Skin, index = 1
	Name = Rib_Root, index = 2
Creating FEA BEM
	Getting quads for BEM!
	Mesh for body = 0
	Number of nodal coordinates = 180
	Number of elements = 194
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 32
	Elemental Quad4 = 162

Getting FEA materials.......
	Number of materials - 1
	Material name - Madeupium
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 2
	Property name - Rib_Root
	Property name - Skin
	Done getting FEA properties

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - edgeConstraint
	No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement"
	Done getting FEA constraints
Support tuple is NULL - No supports applied

Getting FEA loads.......
	Number of loads - 1
	Load name - pressureInternal
	Done getting FEA loads

Analysis tuple is NULL

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file


Writing MYSTRAN instruction file....


Running Mystran......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL

Running PostAnalysis ...... mystran

Executing dataTransfer ......
No variable name provided - defaulting to variable - Displacement

Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Farfield
	Boundary condition name - Skin
	Boundary condition name - SymmPlane
	Done getting CFD boundary conditions
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 180
	Loading displacements for Subcase = 1
No variable name provided - defaulting to variable - Displacement
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 180
	Loading displacements for Subcase = 1
No variable name provided - defaulting to variable - Displacement
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 180
	Loading displacements for Subcase = 1

Running PreAnalysis ...... su2
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Displacement_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../runDirectory_AeroelasticSimple_Displacement_tetgen_tetgenAIM/tetgen_0.su2

---------------- Grid deformation parameters ( Zone 0 )  ----------------
Grid deformation using a linear elasticity method.


-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aeroelasticSimple_Displacement_SM.su2. 
Cell stiffness scaled by distance to nearest solid surface.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+
Three dimensional problem.
22560 grid points.
98725 volume elements.
3 surface markers.
342 boundary elements in index 0 (Marker = BC_1).
12856 boundary elements in index 1 (Marker = BC_2).
11696 boundary elements in index 2 (Marker = BC_3).
98725 tetrahedra.

----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identify edges and vertices.
Setting the bound control volume structure.
Volume of the computational grid: 63999.5.
  Info: Ignoring the following volume output fields/groups:
  SOLUTION
Volume output fields: COORDINATES
  Info: Ignoring the following screen output fields:
  RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME
  Info: Ignoring the following history output groups:
  RMS_RES, AERO_COEFF
History output group(s): ITER, TIME_DOMAIN, WALL_TIME
Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive.
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.

--------------------- Surface grid deformation (ZONE 0) -----------------
Performing the deformation of the surface grid.
Updating the surface coordinates from the input file.

------------------- Volumetric grid deformation (ZONE 0) ----------------
Performing the deformation of the volumetric grid.

WARNING: Convexity is not checked for 3D elements (issue #1171).


----------------------- Write deformed grid files -----------------------
|SU2 mesh                           |aeroelasticSimple_Displacement_SM.su2|
|CSV file                           |surface_deformed.csv               |
|Tecplot binary                     |volume_deformed.szplt              |
|Tecplot binary surface             |surface_deformed.szplt             |
Adding any FFD information to the SU2 file.

------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

Completed in 3.836508 seconds on 1 core.

------------------------- Exit Success (SU2_DEF) ------------------------


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_3.

Surface(s) plotted in the output file: BC_3.
Surface(s) affected by the design variables: BC_3.
Input mesh file name: ../runDirectory_AeroelasticSimple_Displacement_tetgen_tetgenAIM/tetgen_0.su2

--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1. 
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.

--------------- Time Numerical Integration  ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------ Convergence Criteria  ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticSimple_Displacement_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Displacement_SM.
Volume file name: flow_aeroelasticSimple_Displacement_SM.
Restart file name: restart_flow_aeroelasticSimple_Displacement_SM.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+

-------------------- Output Preprocessing ( Zone 0 ) --------------------

WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)

Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
22560 grid points.
98725 volume elements.
3 surface markers.
342 boundary elements in index 0 (Marker = BC_1).
12856 boundary elements in index 1 (Marker = BC_2).
11696 boundary elements in index 2 (Marker = BC_3).
98725 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 63999.5.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 1594.52. Mean K: 49.8216. Standard deviation K: 81.7526.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        14.2921|        84.8436|
|     CV Face Area Aspect Ratio|        1.65091|        10423.3|
|           CV Sub-Volume Ratio|              1|         267774|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     22560|    1/1.00|        10|
|         1|      4201|    1/5.37|   8.56569|
|         2|       997|    1/4.21|    7.9549|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 10.0438 m^2.
Area projection in the x-plane = 0.679139 m^2, y-plane = 0.327414 m^2, z-plane = 4.84583 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380458 m.
Min. coordinate in the x-direction = -0.000478065 m, y-direction = -2.86151e-18 m, z-direction = -0.0467319 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is a single plane.
Computing wall distances.

-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

------------------- Numerics Preprocessing ( Zone 0 ) -------------------

----------------- Integration Preprocessing ( Zone 0 ) ------------------

------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  1.2317e+00|   -1.523025|    0.609925|    0.080721|    3.946081|   -0.718239|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  1.1320e+00|   -1.339928|    1.151012|    0.965895|    4.131543|   -0.220381|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  1.0738e+00|   -1.396967|    1.128043|    1.048458|    4.059504|    2.124723|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  1.0565e+00|   -1.363292|    1.004045|    0.944956|    4.100976|  -17.543179|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.0309e+00|   -1.425272|    0.899661|    0.911531|    4.035349|   -9.050381|

----------------------------- Solver Exit -------------------------------

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.42527|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticSimple_Displacement_SM.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SM.dat).
|CSV file                           |surface_flow_aeroelasticSimple_Displacement_SM.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SM.dat).
|Tecplot binary                     |flow_aeroelasticSimple_Displacement_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SM.dat).
|Tecplot binary surface             |surface_flow_aeroelasticSimple_Displacement_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SM.dat).

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


Running PostAnalysis ...... su2
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.aimName' is deprecated. Please use 'name'!
WARNING: 'capsAnalysis.getAnalysisInfo' is deprecated. Please use 'Analysis.info'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsBound.fillVertexSets' is deprecated. Please use 'None'!
WARNING: 'capsBound.executeTransfer' is deprecated. Please use 'None'!
WARNING: 'capsBound.getDestData' is deprecated. Please use 'vertexSet["name"].dataSet["variableName"].getData'!
WARNING: 'DataSet.getData' is deprecated. Please use 'DataSet.data'!
WARNING: 'capsAnalysis.getAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	0m24.218s
user	0m23.920s
sys	0m3.185s
+ status=0
+ set +x

=================================================
Legacy CAPS verification (using pyCAPS) case aeroelasticSimple_Displacement_SU2_and_Mystran.py passed (as expected)
=================================================


=================================================
+ rm -rf aeroelasticSimple_Iterative_SU2_and_Mystran
+ echo 'aeroelasticSimple_Iterative_SU2_and_Mystran.py test;'
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
aeroelasticSimple_Iterative_SU2_and_Mystran.py test;
+ python -u aeroelasticSimple_Iterative_SU2_and_Mystran.py -verbosity=0 -workDir=runDirectory
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt

Running PreAnalysis ...... egads
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Farfield, index = 1
	Name = SymmPlane, index = 2
	Name = Skin, index = 3
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 0
Getting surface mesh for body 1 (of 1)

Running PostAnalysis ...... egads
Body 1 (of 1)
Number of nodes    = 12449
Number of elements = 24894
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 24894
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 12449
Total number of elements = 24894

Running PreAnalysis ...... tetgen
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Farfield, index = 1
	Name = SymmPlane, index = 2
	Name = Skin, index = 3
Number of surface nodes - 12449
Number of surface elements - 24894
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000T1.00e-16
Delaunizing vertices...
Delaunay seconds:  1.48164
Creating surface mesh ...
Surface mesh seconds:  0.038755
Recovering boundaries...
Boundary recovery seconds:  0.135761
Removing exterior tetrahedra ...
Exterior tets removal seconds:  0.054164
Recovering Delaunayness...
Delaunay recovery seconds:  0.061364
Refining mesh...
  16594 insertions, added 9161 points, 329937 tetrahedra in queue.
  5525 insertions, added 645 points, 61689 tetrahedra in queue.
  7365 insertions, added 233 points, 1286 tetrahedra in queue.
Refinement seconds:  2.91984
Smoothing vertices...
Mesh smoothing seconds:  1.8169
Improving mesh...
Mesh improvement seconds:  0.055412

Writing nodes.
Writing elements.
Writing faces.
Writing edges.

Output seconds:  0.015294
Total running seconds:  6.57977

Statistics:

  Input points: 12449
  Input facets: 24894
  Input segments: 37341
  Input holes: 0
  Input regions: 0

  Mesh points: 22560
  Mesh tetrahedra: 98725
  Mesh faces: 209897
  Mesh faces on exterior boundary: 24894
  Mesh faces on input facets: 24894
  Mesh edges on input segments: 37341
  Steiner points inside domain: 10111

Done meshing using TetGen!
No project name ("Proj_Name") provided - A volume mesh will not be written out

Running PostAnalysis ...... tetgen


Executing dataTransfer "Displacement"......

Running PreAnalysis ...... su2

Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Farfield
	Boundary condition name - Skin
	Boundary condition name - SymmPlane
	Done getting CFD boundary conditions
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_3.

Surface(s) plotted in the output file: BC_3.
Surface(s) affected by the design variables: BC_3.
Input mesh file name: ../runDirectory_AeroelasticSimple_Iterative_tetgen_tetgenAIM/tetgen_0.su2

--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1. 
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.

--------------- Time Numerical Integration  ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------ Convergence Criteria  ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_SM.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+

-------------------- Output Preprocessing ( Zone 0 ) --------------------

WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)

Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
22560 grid points.
98725 volume elements.
3 surface markers.
342 boundary elements in index 0 (Marker = BC_1).
12856 boundary elements in index 1 (Marker = BC_2).
11696 boundary elements in index 2 (Marker = BC_3).
98725 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 63999.5.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 1594.52. Mean K: 49.8216. Standard deviation K: 81.7526.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        14.2921|        84.8436|
|     CV Face Area Aspect Ratio|        1.65091|        10423.3|
|           CV Sub-Volume Ratio|              1|         267774|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     22560|    1/1.00|        10|
|         1|      4201|    1/5.37|   8.56569|
|         2|       997|    1/4.21|    7.9549|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 10.0438 m^2.
Area projection in the x-plane = 0.679139 m^2, y-plane = 0.327414 m^2, z-plane = 4.84583 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380458 m.
Min. coordinate in the x-direction = -0.000478065 m, y-direction = -2.86151e-18 m, z-direction = -0.0467319 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is a single plane.
Computing wall distances.

-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

------------------- Numerics Preprocessing ( Zone 0 ) -------------------

----------------- Integration Preprocessing ( Zone 0 ) ------------------

------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  9.9230e-01|   -1.523025|    0.609925|    0.080721|    3.946081|   -0.718239|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  1.0243e+00|   -1.339928|    1.151012|    0.965895|    4.131543|   -0.220381|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  1.0170e+00|   -1.396967|    1.128043|    1.048458|    4.059504|    2.124723|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  1.0103e+00|   -1.363292|    1.004045|    0.944956|    4.100976|  -17.543179|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.0272e+00|   -1.425272|    0.899661|    0.911531|    4.035349|   -9.050381|

----------------------------- Solver Exit -------------------------------

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.42527|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticSimple_Iterative_SM.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file                           |surface_flow_aeroelasticSimple_Iterative_SM.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary                     |flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface             |surface_flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


Running PostAnalysis ...... su2


Executing dataTransfer "Pressure"......
Mapping Csys attributes ................
	Number of unique Csys attributes = 0

Getting FEA coordinate systems.......
	Number of coordinate systems - 0
	No coordinate systems found - defaulting to global
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = Rib_Root, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 1
	Name = Skin, index = 1
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 3
	Name = Skin_Top, index = 1
	Name = Skin_Bottom, index = 2
	Name = Skin_Tip, index = 3
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Skin, index = 1
	Name = Rib_Root, index = 2
Creating FEA BEM
	Getting quads for BEM!
	Mesh for body = 0
	Number of nodal coordinates = 12
	Number of elements = 12
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 4
	Elemental Quad4 = 8

Getting FEA materials.......
	Number of materials - 1
	Material name - Madeupium
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 2
	Property name - Rib_Root
	Property name - Skin
	Done getting FEA properties

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - edgeConstraint
	No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement"
	Done getting FEA constraints
Support tuple is NULL - No supports applied

Getting FEA loads.......
	Number of loads - 1
	Load name - pressureAero
	No "groupName" specified for Load tuple pressureAero, going to use load name
	Done getting FEA loads

Analysis tuple is NULL
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 5887
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 5887
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 5887

Running PreAnalysis ...... mystran
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 4 (total = 4)
	TransferName = Skin_Bottom
	Number of Elements = 4 (total = 8)
	TransferName = Skin_Tip
	Number of Elements = 2 (total = 10)

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file


Writing MYSTRAN instruction file....


Running Mystran......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL

Running PostAnalysis ...... mystran


Executing dataTransfer "Displacement"......
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 12
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 12
	Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
	Number of Grid Points = 12
	Loading displacements for Subcase = 1

Running PreAnalysis ...... su2
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../runDirectory_AeroelasticSimple_Iterative_tetgen_tetgenAIM/tetgen_0.su2

---------------- Grid deformation parameters ( Zone 0 )  ----------------
Grid deformation using a linear elasticity method.


-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aeroelasticSimple_Iterative_SM.su2. 
Cell stiffness scaled by distance to nearest solid surface.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+
Three dimensional problem.
22560 grid points.
98725 volume elements.
3 surface markers.
342 boundary elements in index 0 (Marker = BC_1).
12856 boundary elements in index 1 (Marker = BC_2).
11696 boundary elements in index 2 (Marker = BC_3).
98725 tetrahedra.

----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identify edges and vertices.
Setting the bound control volume structure.
Volume of the computational grid: 63999.5.
  Info: Ignoring the following volume output fields/groups:
  SOLUTION
Volume output fields: COORDINATES
  Info: Ignoring the following screen output fields:
  RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME
  Info: Ignoring the following history output groups:
  RMS_RES, AERO_COEFF
History output group(s): ITER, TIME_DOMAIN, WALL_TIME
Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive.
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.

--------------------- Surface grid deformation (ZONE 0) -----------------
Performing the deformation of the surface grid.
Updating the surface coordinates from the input file.

------------------- Volumetric grid deformation (ZONE 0) ----------------
Performing the deformation of the volumetric grid.

WARNING: Convexity is not checked for 3D elements (issue #1171).


----------------------- Write deformed grid files -----------------------
|SU2 mesh                           |aeroelasticSimple_Iterative_SM.su2 |
|CSV file                           |surface_deformed.csv               |
|Tecplot binary                     |volume_deformed.szplt              |
|Tecplot binary surface             |surface_deformed.szplt             |
Adding any FFD information to the SU2 file.

------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

Completed in 4.892896 seconds on 1 core.

------------------------- Exit Success (SU2_DEF) ------------------------


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| 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 for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_3.

Surface(s) plotted in the output file: BC_3.
Surface(s) affected by the design variables: BC_3.
Input mesh file name: ../runDirectory_AeroelasticSimple_Iterative_tetgen_tetgenAIM/tetgen_0.su2

--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1. 
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.

--------------- Time Numerical Integration  ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------ Convergence Criteria  ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_SM.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_3|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_1|
+-----------------------------------------------------------------------+
|                     Symmetry plane|                               BC_2|
+-----------------------------------------------------------------------+

-------------------- Output Preprocessing ( Zone 0 ) --------------------

WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)

Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
22560 grid points.
98725 volume elements.
3 surface markers.
342 boundary elements in index 0 (Marker = BC_1).
12856 boundary elements in index 1 (Marker = BC_2).
11696 boundary elements in index 2 (Marker = BC_3).
98725 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 63999.5.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 1594.52. Mean K: 49.8216. Standard deviation K: 81.7526.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        14.2921|        84.8436|
|     CV Face Area Aspect Ratio|        1.65091|        10423.3|
|           CV Sub-Volume Ratio|              1|         267774|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     22560|    1/1.00|        10|
|         1|      4201|    1/5.37|   8.56569|
|         2|       997|    1/4.21|    7.9549|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 10.0438 m^2.
Area projection in the x-plane = 0.679139 m^2, y-plane = 0.327414 m^2, z-plane = 4.84583 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380458 m.
Min. coordinate in the x-direction = -0.000478065 m, y-direction = -2.86151e-18 m, z-direction = -0.0467319 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is a single plane.
Computing wall distances.

-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

------------------- Numerics Preprocessing ( Zone 0 ) -------------------

----------------- Integration Preprocessing ( Zone 0 ) ------------------

------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  1.2079e+00|   -1.523025|    0.609925|    0.080721|    3.946081|   -0.718239|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  1.1816e+00|   -1.339928|    1.151012|    0.965895|    4.131543|   -0.220381|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  1.2199e+00|   -1.396967|    1.128043|    1.048458|    4.059504|    2.124723|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  1.2072e+00|   -1.363292|    1.004045|    0.944956|    4.100976|  -17.543179|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.1989e+00|   -1.425272|    0.899661|    0.911531|    4.035349|   -9.050381|

----------------------------- Solver Exit -------------------------------

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.42527|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticSimple_Iterative_SM.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file                           |surface_flow_aeroelasticSimple_Iterative_SM.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary                     |flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface             |surface_flow_aeroelasticSimple_Iterative_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


Running PostAnalysis ...... su2


Executing dataTransfer "Pressure"......
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 5887
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 5887
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
	Number of variables = 13
	Number of data points = 5887

Running PreAnalysis ...... mystran
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 4 (total = 4)
	TransferName = Skin_Bottom
	Number of Elements = 4 (total = 8)
	TransferName = Skin_Tip
	Number of Elements = 2 (total = 10)

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file


Writing MYSTRAN instruction file....


Running Mystran......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL

Running PostAnalysis ...... mystran
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.getAnalysisInfo' is deprecated. Please use 'Analysis.info'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsBound.fillVertexSets' is deprecated. Please use 'None'!
WARNING: 'capsBound.executeTransfer' is deprecated. Please use 'None'!
WARNING: 'capsBound.getDestData' is deprecated. Please use 'vertexSet["name"].dataSet["variableName"].getData'!
WARNING: 'DataSet.getData' is deprecated. Please use 'DataSet.data'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	0m38.456s
user	0m35.789s
sys	0m4.542s
+ status=0
+ set +x

=================================================
Legacy CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_SU2_and_Mystran.py passed (as expected)
=================================================


*************************************************
*************************************************

=================================================
Legacy Did not run examples for:

Astros
=================================================

All tests pass!

[Execution node] check if [reynolds] is in [[windows10x64]]
Run condition [Execution node ] preventing perform for step [Execute Windows batch command]
[GNU C Compiler (gcc)] Sleeping for 5 seconds due to JENKINS-32191...
[GNU C Compiler (gcc)] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining
[Clang] Sleeping for 5 seconds due to JENKINS-32191...
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[Clang] Skipping post processing
[Clang] No filter has been set, publishing all 0 issues
[Clang] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.6,CAPS/AEROELASTIC,LINUX64,reynolds)
[Static Analysis] Using reference build 'ESP_RegCaps/CASREV=7.6,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=LINUX64,buildnode=reynolds #432' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1
[Static Analysis] -> All quality gates have been passed
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_RegCaps/CASREV=7.6,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=LINUX64,buildnode=reynolds #433'.
[Checks API] No suitable checks publisher found.
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] done
Finished: SUCCESS