Console Output

Skipping 1,524 KB.. Full Log
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.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 0.368969 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.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative.
Volume file name: flow_aeroelasticSimple_Iterative.
Restart file name: restart_flow_aeroelasticSimple_Iterative.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.
5335 grid points.
21418 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6898 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21418 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: 0.0597577. Standard deviation K: 0.944969.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        13.3625|        83.7803|
|     CV Face Area Aspect Ratio|        1.73115|        1815.24|
|           CV Sub-Volume Ratio|              1|    2.75713e+32|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      5335|    1/1.00|        10|
|         1|       969|    1/5.51|   8.49482|
|         2|       188|    1/5.15|   7.37661|
+-------------------------------------------+
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|  7.4846e-02|   -0.347856|    1.967459|    1.613778|    5.121250|   -2.448060|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  7.4010e-02|   -0.312631|    2.018247|    2.024655|    5.150322|   -2.910398|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  7.4438e-02|   -0.633188|    2.011024|    2.030124|    4.851553|   -3.071838|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.633188|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticSimple_Iterative.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat).
|CSV file                           |surface_flow_aeroelasticSimple_Iterative.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat).
|Tecplot binary                     |flow_aeroelasticSimple_Iterative.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat).
|Tecplot binary surface             |surface_flow_aeroelasticSimple_Iterative.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.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 =  -0.621016
Cd =  0.202164

real	0m7.872s
user	0m7.259s
sys	0m1.223s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_SU2_and_Astros.py passed (as expected)
=================================================


=================================================
+ echo 'aeroelastic_Iterative_SU2_and_Astros.py test;'
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
aeroelastic_Iterative_SU2_and_Astros.py test;
+ python -u aeroelastic_Iterative_SU2_and_Astros.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt

Running PreAnalysis ...... su2
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)
Body 1 (of 1)
Number of nodes    = 8968
Number of elements = 17932
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17932
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 8968
Total number of elements = 17932
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 - 8968
Number of surface elements - 17932
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

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 - aeroelastic_Iterative_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: ../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_aeroelastic_Iterative.dat.
Surface file name: surface_flow_aeroelastic_Iterative.
Volume file name: flow_aeroelastic_Iterative.
Restart file name: restart_flow_aeroelastic_Iterative.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.
13675 grid points.
55046 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
17856 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
55046 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: 0.0233245. Standard deviation K: 0.591062.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        7.92092|        83.4688|
|     CV Face Area Aspect Ratio|        1.79099|        4487.59|
|           CV Sub-Volume Ratio|              1|        51266.6|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     13675|    1/1.00|        10|
|         1|      2482|    1/5.51|   8.49277|
|         2|       466|    1/5.33|   7.29461|
+-------------------------------------------+
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|  1.9846e-01|   -0.552253|    1.763063|    1.409381|    4.916853|   -2.401454|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  2.0054e-01|   -0.591221|    1.823499|    1.754334|    4.878314|   -2.682314|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  2.0087e-01|   -0.750602|    1.822484|    1.872264|    4.714713|   -2.919199|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.750602|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelastic_Iterative.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|CSV file                           |surface_flow_aeroelastic_Iterative.csv|

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|Tecplot binary                     |flow_aeroelastic_Iterative.szplt   |

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|Tecplot binary surface             |surface_flow_aeroelastic_Iterative.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.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
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 = 0
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 capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Ribs_and_Spars, index = 1
	Name = Skin, index = 2
	Name = Rib_Root, index = 3
Creating FEA BEM
	Getting quads for BEM!
	Mesh for body = 0
	Number of nodal coordinates = 131
	Number of elements = 188
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 40
	Elemental Quad4 = 148

Getting FEA materials.......
	Number of materials - 2
	Material name - Madeupium
	Material name - Unobtainium
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 3
	Property name - Rib_Root
	Property name - Ribs_and_Spars
	Property name - Skin
	Done getting FEA properties
Updating mesh element types based on properties input

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
Connect tuple is NULL - Using defaults

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
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Default
	Done getting FEA analyses
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 3.118352e+09, tgt = 3.118352e+09, diff = 2.548881e+00
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 3.022500e+09, tgt = 3.022500e+09, diff = 2.450226e+01
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 3.798000e+07, tgt = 3.797999e+07, diff = 9.175738e+00
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 48 (total = 48)
	TransferName = Skin_Bottom
	Number of Elements = 48 (total = 96)
	TransferName = Skin_Tip
	Number of Elements = 12 (total = 108)

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

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint cards--each subcase individually
	Writing load cards
	Writing material cards
	Writing property cards
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelastic_Iterative_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: aeroelastic_Iterative.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.
13675 grid points.
55046 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
17856 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
55046 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                           |aeroelastic_Iterative.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 1.507841 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_aeroelastic_Iterative.dat.
Surface file name: surface_flow_aeroelastic_Iterative.
Volume file name: flow_aeroelastic_Iterative.
Restart file name: restart_flow_aeroelastic_Iterative.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.
13675 grid points.
55046 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
17856 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
55046 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: 0.0233245. Standard deviation K: 0.591062.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        7.92092|        83.4688|
|     CV Face Area Aspect Ratio|        1.79099|        4487.59|
|           CV Sub-Volume Ratio|              1|        51266.6|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     13675|    1/1.00|        10|
|         1|      2482|    1/5.51|   8.49277|
|         2|       466|    1/5.33|   7.29461|
+-------------------------------------------+
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|  1.9865e-01|   -0.552253|    1.763063|    1.409381|    4.916853|   -2.401454|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  2.0071e-01|   -0.591221|    1.823499|    1.754334|    4.878314|   -2.682314|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  2.0099e-01|   -0.750602|    1.822484|    1.872264|    4.714713|   -2.919199|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.750602|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelastic_Iterative.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|CSV file                           |surface_flow_aeroelastic_Iterative.csv|

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|Tecplot binary                     |flow_aeroelastic_Iterative.szplt   |

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|Tecplot binary surface             |surface_flow_aeroelastic_Iterative.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.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_aeroelastic_Iterative.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 3.118352e+09, tgt = 3.118352e+09, diff = 2.548881e+00
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 3.022500e+09, tgt = 3.022500e+09, diff = 2.450226e+01
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 3.798000e+07, tgt = 3.797999e+07, diff = 9.175738e+00
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 48 (total = 48)
	TransferName = Skin_Bottom
	Number of Elements = 48 (total = 96)
	TransferName = Skin_Tip
	Number of Elements = 12 (total = 108)

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

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint cards--each subcase individually
	Writing load cards
	Writing material cards
	Writing property cards
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelastic_Iterative_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: aeroelastic_Iterative.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.
13675 grid points.
55046 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
17856 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
55046 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                           |aeroelastic_Iterative.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 1.503482 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_aeroelastic_Iterative.dat.
Surface file name: surface_flow_aeroelastic_Iterative.
Volume file name: flow_aeroelastic_Iterative.
Restart file name: restart_flow_aeroelastic_Iterative.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.
13675 grid points.
55046 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
17856 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
55046 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: 0.0233245. Standard deviation K: 0.591062.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        7.92092|        83.4688|
|     CV Face Area Aspect Ratio|        1.79099|        4487.59|
|           CV Sub-Volume Ratio|              1|        51266.6|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     13675|    1/1.00|        10|
|         1|      2482|    1/5.51|   8.49277|
|         2|       466|    1/5.33|   7.29461|
+-------------------------------------------+
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|  1.9854e-01|   -0.552253|    1.763063|    1.409381|    4.916853|   -2.401454|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  2.0060e-01|   -0.591221|    1.823499|    1.754334|    4.878314|   -2.682314|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  2.0098e-01|   -0.750602|    1.822484|    1.872264|    4.714713|   -2.919199|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.750602|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelastic_Iterative.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|CSV file                           |surface_flow_aeroelastic_Iterative.csv|

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|Tecplot binary                     |flow_aeroelastic_Iterative.szplt   |

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|Tecplot binary surface             |surface_flow_aeroelastic_Iterative.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.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_aeroelastic_Iterative.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 3.118352e+09, tgt = 3.118352e+09, diff = 2.548881e+00
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 3.022500e+09, tgt = 3.022500e+09, diff = 2.450226e+01
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 13
	Number of data points = 25
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 3.798000e+07, tgt = 3.797999e+07, diff = 9.175738e+00
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 48 (total = 48)
	TransferName = Skin_Bottom
	Number of Elements = 48 (total = 96)
	TransferName = Skin_Tip
	Number of Elements = 12 (total = 108)

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

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint cards--each subcase individually
	Writing load cards
	Writing material cards
	Writing property cards
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelastic_Iterative_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: aeroelastic_Iterative.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.
13675 grid points.
55046 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
17856 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
55046 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                           |aeroelastic_Iterative.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 1.502075 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_aeroelastic_Iterative.dat.
Surface file name: surface_flow_aeroelastic_Iterative.
Volume file name: flow_aeroelastic_Iterative.
Restart file name: restart_flow_aeroelastic_Iterative.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.
13675 grid points.
55046 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
17856 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
55046 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: 0.0233245. Standard deviation K: 0.591062.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        7.92092|        83.4688|
|     CV Face Area Aspect Ratio|        1.79099|        4487.59|
|           CV Sub-Volume Ratio|              1|        51266.6|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     13675|    1/1.00|        10|
|         1|      2482|    1/5.51|   8.49277|
|         2|       466|    1/5.33|   7.29461|
+-------------------------------------------+
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|  1.9864e-01|   -0.552253|    1.763063|    1.409381|    4.916853|   -2.401454|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  2.0069e-01|   -0.591221|    1.823499|    1.754334|    4.878314|   -2.682314|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  2.0100e-01|   -0.750602|    1.822484|    1.872264|    4.714713|   -2.919199|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.750602|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelastic_Iterative.dat|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|CSV file                           |surface_flow_aeroelastic_Iterative.csv|

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|Tecplot binary                     |flow_aeroelastic_Iterative.szplt   |

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat).
|Tecplot binary surface             |surface_flow_aeroelastic_Iterative.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.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

real	0m24.807s
user	0m29.391s
sys	0m6.529s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case aeroelastic_Iterative_SU2_and_Astros.py passed (as expected)
=================================================

Running.... CORSAIRLITE PyTests


=================================================
+ echo 'gp.py test;'
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
gp.py test;
+ python -u gp.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt

Objective
---------
   0.00713 dimensionless

Variables
---------
   x  :   3.00000   [-]   The X variable
   y  :  81.00008   [-]   The Y variable
   z  :   0.19245   [-]   The Z variable

Sensitivities
-------------
   No Constants in the Formulation

Solve Report
------------
   Solve Method           :  Geometric Program 
   Classification         :  Convex 
   Solver                 :  cvxopt 


real	0m2.552s
user	0m1.548s
sys	0m0.084s
+ status=0
+ set +x

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


=================================================
+ echo 'qp.py test;'
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
qp.py test;
+ python -u qp.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt

Objective
---------
   -21.56250 dimensionless

Variables
---------
   x  :  1.62500   [-]   The X variable
   y  :  1.37500   [-]   The Y variable

Constants
---------
   c   :  3         [-]   A constant
   c2  :  2         [-]   A constant

Sensitivities
-------------
   c   :  + 0.46957   A constant
   c2  :  - 0.22338   A constant

Solve Report
------------
   Solve Method           :  Quadratic Program 
   Classification         :  Convex 
   Solver                 :  cvxopt 


real	0m0.778s
user	0m1.053s
sys	0m0.027s
+ status=0
+ set +x

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


=================================================
+ echo 'sp.py test;'
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
sp.py test;
+ python -u sp.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt

Objective
---------
   0.45721 dimensionless

Variables
---------
   x  :  2.56155   [-]   The X variable
   y  :  6.56155   [-]   The Y variable
   z  :  1.17116   [-]   The Z variable

Constants
---------
   c  :  2         [-]   A constant

Sensitivities
-------------
   Sensitivities not computed

Solve Report
------------
   Solve Method           :  Signomial Program--Standard 
   Classification         :  Iterative 
   Solver                 :  cvxopt 
   Number of Iterations   :  3 
   Termination Status     :  Converged, relative error (3.15e-04) is less than specified tolerance (1.00e-03) 


real	0m0.754s
user	0m1.030s
sys	0m0.026s
+ status=0
+ set +x

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


=================================================
+ echo 'boydBox.py test;'
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
boydBox.py test;
+ python -u boydBox.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt

Objective
---------
   0.00520 1 / meter ** 3

Variables
---------
   d  :  11.26658   meter   The Z variable
   h  :   2.92246   meter   The Y variable
   w  :   5.84486   meter   The X variable

Constants
---------
   Aflr   :  1000         meter ** 2   Area of floor          
   Awall  :   100         meter ** 2   Area of wall           
   alpha  :     0.50000      [-]       Aspect Ratio Constraint
   beta   :     2            [-]       Aspect Ratio Constraint
   delta  :     2            [-]       Aspect Ratio Constraint
   gamma  :     0.50000      [-]       Aspect Ratio Constraint

Sensitivities
-------------
   Sensitivities not computed

Solve Report
------------
   Solve Method           :  Geometric Program 
   Classification         :  Convex 
   Solver                 :  cvxopt 


real	0m0.649s
user	0m0.926s
sys	0m0.025s
+ status=0
+ set +x

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


=================================================
+ echo 'hoburg_gp.py test;'
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
hoburg_gp.py test;
+ python -u hoburg_gp.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt

Objective
---------
   5885.20993 newton

Variables
---------
   AR          :        20.42440        [-]         aspect ratio                                                            
   C_D_0       :         0.01268        [-]         Drag Coefficient, segment 0                                             
   C_D_1       :         0.01269        [-]         Drag Coefficient, segment 1                                             
   C_D_2       :         0.00777        [-]         Drag Coefficient, segment 2                                             
   C_Dfuse_0   :         0.00180        [-]         Fuselage Drag Coefficient, segment 0                                    
   C_Dfuse_1   :         0.00180        [-]         Fuselage Drag Coefficient, segment 1                                    
   C_Dfuse_2   :         0.00180        [-]         Fuselage Drag Coefficient, segment 2                                    
   C_Di_0      :         0.00542        [-]         Induced Drag Coefficient, segment 0                                     
   C_Di_1      :         0.00542        [-]         Induced Drag Coefficient, segment 1                                     
   C_Di_2      :         0.00023        [-]         Induced Drag Coefficient, segment 2                                     
   C_Dp_0      :         0.00546        [-]         Wing Profile Drag Coefficient, segment 0                                
   C_Dp_1      :         0.00547        [-]         Wing Profile Drag Coefficient, segment 1                                
   C_Dp_2      :         0.00573        [-]         Wing Profile Drag Coefficient, segment 2                                
   C_L_0       :         0.57472        [-]         Lift Coefficient, segment 0                                             
   C_L_1       :         0.57468        [-]         Lift Coefficient, segment 1                                             
   C_L_2       :         0.11884        [-]         Lift Coefficient, segment 2                                             
   I_cap_bar   :         0.00002        [-]         Area moment of inertia of cap on 2D cross section, normalized by chord^4
   M_r_bar     :     36229.99291       newton       Root Bending unit per unit chord                                        
   P_max       :   1183881.78586        watt        Maximum Engine Power                                                    
   R           :      4999.98639     kilometer      Single Segment range                                                    
   Re_0        :   4649061.20108        [-]         Reynolds Number, segment 0                                              
   Re_1        :   4450813.35353        [-]         Reynolds Number, segment 1                                              
   Re_2        :  10223708.47802        [-]         Reynolds Number, segment 2                                              
   S           :        27.74208     meter ** 2     total wing area                                                         
   T_0         :       743.85020       newton       Thrust, segment 0                                                       
   T_1         :       682.52757       newton       Thrust, segment 1                                                       
   T_2         :      2204.87369       newton       Thrust, segment 2                                                       
   V_0         :        68.21331   meter / second   Velocity, segment 0                                                     
   V_1         :        65.30452   meter / second   Velocity, segment 1                                                     
   V_2         :       150.00729   meter / second   Velocity, segment 2                                                     
   V_stall     :        37.99887   meter / second   stall speed                                                             
   W_0         :     33722.73965       newton       Weight, segment 0                                                       
   W_1         :     30906.28806       newton       Weight, segment 1                                                       
   W_2         :     33722.72495       newton       Weight, segment 2                                                       
   W_MTO       :     36802.52748       newton       Maximum Takeoff Weight                                                  
   W_cap       :      4109.85677       newton       Weight of Wing Spar Cap                                                 
   W_eng       :      2802.40879       newton       Engine Weight                                                           
   W_fuel_out  :      3068.88956       newton       Weight of fuel, outbound                                                
   W_fuel_ret  :      2816.31841       newton       Weight of fuel, return                                                  
   W_pay       :      4905.19291       newton       Payload Weight                                                          
   W_tilde     :     22406.17658       newton       Dry Weight, no wing                                                     
   W_web       :       140.16532       newton       Weight of Wing Spar Shear Web                                           
   W_wing      :      8499.81607       newton       wing weight                                                             
   W_zfw       :     30906.02219       newton       Zero Fuel Weight                                                        
   eta_0_0     :         0.27005        [-]         Overall Efficiency, segment 0                                           
   eta_0_1     :         0.27002        [-]         Overall Efficiency, segment 1                                           
   eta_0_2     :         0.27947        [-]         Overall Efficiency, segment 2                                           
   eta_i_0     :         0.90772        [-]         Inviscid Propeller Efficiency, segment 0                                
   eta_i_1     :         0.90763        [-]         Inviscid Propeller Efficiency, segment 1                                
   eta_i_2     :         0.93941        [-]         Inviscid Propeller Efficiency, segment 2                                
   eta_prop_0  :         0.77156        [-]         Propeller Efficiency, segment 0                                         
   eta_prop_1  :         0.77149        [-]         Propeller Efficiency, segment 1                                         
   eta_prop_2  :         0.79850        [-]         Propeller Efficiency, segment 2                                         
   nu          :         0.78604        [-]         Placeholder, (1+lam_w+lam_w**2)/(1+lam_w)**2                            
   p           :         1.90003        [-]         Dummy Variable (1+2*lam_w)                                              
   q           :         1.45003        [-]         Dummy Variable (1+lam_w)                                                
   t_cap_bar   :         0.00458        [-]         Spar cap thickness per unit chord                                       
   t_web_bar   :         0.00069        [-]         Spar web thickness per unit chord                                       
   tau         :         0.15000        [-]         airfoil thickness to chord ratio                                        
   z_bre_0     :         0.08710        [-]         Breguet Range Factor, segment 0                                         
   z_bre_1     :         0.08721        [-]         Breguet Range Factor, segment 1                                         

Constants
---------
   A_prop           :         0.78500           meter ** 2          Disk area of propeller                             
   CDA0             :         0.05000           meter ** 2          fuselage drag area                                 
   C_Lmax           :         1.50000              [-]              max CL with flaps down                             
   N_lift           :         6                    [-]              Ultimate Load Factor                               
   W_fixed          :     14700                   newton            fixed weight                                       
   e                :         0.95000              [-]              Oswald efficiency factor                           
   eta_eng          :         0.35000              [-]              Engine Efficiency                                  
   eta_v            :         0.85000              [-]              Propeller Viscous Efficiency                       
   f_wadd           :         2                    [-]              Added Weight Fraction                              
   g                :         9.81000      meter / second ** 2      Gravitational constant                             
   h_fuel           :  46000000              joule / kilogram       Fuel Specific energy density                       
   k_ew             :         0.03720     newton / watt ** 0.803    Constant for engine weight                         
   mu               :         0.00002   kilogram / meter / second   viscosity of air                                   
   r_h              :         0.75000              [-]              Ratio of height at rear spar to maximum wing height
   rho              :         0.90912     kilogram / meter ** 3     density of air                                     
   rho_SL           :         1.22500     kilogram / meter ** 3     density of air, sea level                          
   rho_cap          :      2700           kilogram / meter ** 3     Density of wing cap material (aluminum)            
   rho_web          :      2700           kilogram / meter ** 3     Density of wing web material (aluminum)            
   sigma_max        :       310                 megapascal          Allowable tensile stress of aluminum               
   sigma_max_shear  :       167                 megapascal          Allowable shear stress of aluminum                 
   w_bar            :         0.50000              [-]              Ratio of spar box width to chord length            

Sensitivities
-------------
   Sensitivities not computed

Solve Report
------------
   Solve Method           :  Geometric Program 
   Classification         :  Convex 
   Solver                 :  cvxopt 


real	0m5.782s
user	0m6.047s
sys	0m0.032s
+ status=0
+ set +x

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

Traceback (most recent call last):
  File "<string>", line 1, in <module>
ModuleNotFoundError: No module named 'scipy'

=================================================
+ echo 'pyCAPS/sizeWing.py test;'
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
pyCAPS/sizeWing.py test;
+ python -u pyCAPS/sizeWing.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
nrock 2

Objective
---------
   0.075 dimensionless

Variables
---------
   AR     :  10.000        [-]         Wing aspect ratio
   CD     :   0.075        [-]         Drag Coefficient 
   CL     :   0.999        [-]         Lift Coefficient 
   S      :   2.642     meter ** 2     Wing area        
   V      :   2.722   meter / second   Airspeed         
   W      :  11.979       newton       Aircraft weight  
   Wwing  :   1.598       newton       Wing weight      

Constants
---------
   ARmax     :  10                [-]            Max AR                                         
   CD0       :   0.040            [-]            Profile drag                                   
   CLmax     :   1                [-]            Max CL                                         
   E0        :  10               joule           Maximum elastic potential energy in rubber band
   Wfixed    :   0.100           newton          Weight of fixed components                     
   Wrock     :   2               newton          Weight of each rock                            
   e         :   0.900            [-]            Oswawld efficiency factor                      
   g         :   9.810    meter / second ** 2    Gravitational constant                         
   nrock     :   2                [-]            Number of rocks to carry                       
   rho       :   1.225   kilogram / meter ** 3   Density of air                                 
   rho_wing  :   1       kilogram / meter ** 3   Weight density of wing                         
   tau       :   0.120            [-]            Airfoil thickness as t/c                       

Sensitivities
-------------
   Sensitivities not computed

Solve Report
------------
   Solve Method           :  Geometric Program 
   Classification         :  Convex 
   Solver                 :  cvxopt 

Optimized L/D: 13.267784561972135
 EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close!

real	0m0.830s
user	0m1.088s
sys	0m0.043s
+ status=0
+ set +x

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

avl: /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/bin/avl

=================================================
+ echo 'pyCAPS/optTaperAvl.py test;'
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
pyCAPS/optTaperAvl.py test;
+ python -u pyCAPS/optTaperAvl.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)

Objective
---------
   1.00805 dimensionless

Variables
---------
   e    :  0.99202   [-]   Oswald efficiency factor
   lam  :  0.39881   [-]   Wing taper ratio        

Sensitivities
-------------
   Sensitivities not available for optimizations of type Sequential Log Convex Program 

Solve Report
------------
   Solve Method           :  Sequential Log Convex Program 
   Classification         :  Iterative 
   Solver                 :  cvxopt 
   Number of Iterations   :  6 
   Termination Status     :  Converged, gradient of Lagrangian (5.888780e-08) within tolerance (1.000000e-06)  

Messages
--------
   1. Wolfe Condition 1 failed at iteration 5 (Step 5).  Watchdog counter is 1


real	0m2.955s
user	0m2.288s
sys	0m0.874s
+ status=0
+ set +x

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


=================================================
+ echo 'pyCAPS/optWingAvl.py test;'
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
pyCAPS/optWingAvl.py test;
+ python -u pyCAPS/optWingAvl.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt
nrock 2
0.4 10.0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
0.9920154828917351 dimensionless [<Quantity(-0.000582398267023887, 'dimensionless')>, <Quantity(-0.0013839124763537214, 'dimensionless')>]
[<Quantity(0.9920154828917351, 'dimensionless')>, [<Quantity(-0.000582398267023887, 'dimensionless')>, <Quantity(-0.0013839124763537214, 'dimensionless')>]]
0.3999711212012575 9.99999999867028
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
0.9920155005982954 dimensionless [<Quantity(-0.0005679852699391752, 'dimensionless')>, <Quantity(-0.0013837638701008625, 'dimensionless')>]
[<Quantity(0.9920155005982954, 'dimensionless')>, [<Quantity(-0.0005679852699391752, 'dimensionless')>, <Quantity(-0.0013837638701008625, 'dimensionless')>]]
0.3999303524733339 9.999999999625928
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = wing, index = 1
Getting vortex lattice surface data
	VLM surface name - wing
	No "groupName" variable provided or no matches found, going to use tuple name
	Done getting vortex lattice surface data
Writing surface - wing (ID = 0)
	Section 1 of 3 (ID = 0)
	Section 2 of 3 (ID = 1)
	Section 3 of 3 (ID = 2)
0.9920155247150121 dimensionless [<Quantity(-0.0005483843692200008, 'dimensionless')>, <Quantity(-0.0013836874790867926, 'dimensionless')>]
[<Quantity(0.9920155247150121, 'dimensionless')>, [<Quantity(-0.0005483843692200008, 'dimensionless')>, <Quantity(-0.0013836874790867926, 'dimensionless')>]]

Objective
---------
   0.072 dimensionless

Variables
---------
   AR     :  10.000        [-]         Wing aspect ratio       
   CD     :   0.072        [-]         Drag Coefficient        
   CL     :   1.000        [-]         Lift Coefficient        
   S      :   0.664     meter ** 2     Wing area               
   V      :   3.600   meter / second   Airspeed                
   W      :   5.270       newton       Aircraft weight         
   Wwing  :   0.201       newton       Wing weight             
   e      :   0.992        [-]         Oswald efficiency factor
   lam    :   0.400        [-]         Wing taper ratio        

Sensitivities
-------------
   Sensitivities not available for optimizations of type Sequential Log Convex Program 

Solve Report
------------
   Solve Method           :  Sequential Log Convex Program 
   Classification         :  Iterative 
   Solver                 :  cvxopt 
   Number of Iterations   :  2 
   Termination Status     :  Converged, magnitude of step (4.08e-05) is witin specified tolerance (1.00e-04) 

Messages
--------
   1. Wolfe Condition 1 failed at iteration 1 (Step 1).  Watchdog counter is 1

13.872090334855463

real	0m2.579s
user	0m2.184s
sys	0m0.660s
+ status=0
+ set +x

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


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

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

avl_OpenMDAO_3_PyTest.py
awave
mses_OpenMDAO_3_PyTest.py
autoLink
Pointwise
cart3d_OpenMDAO_3_alpha_PyTest.py
cart3d_OpenMDAO_3_twist_PyTest.py
Fun3D
Nastran
Mystran
Mystran
=================================================

All tests pass!


=================================================
=================================================
+ cd /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen
+ mkdir -p /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/test/plugs
+ cd /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/test/plugs
+ find /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs -name 'plugs0*.csm'
+ sort -f
+ awk '{ n=split($0, a, ";"); for(i=1; i<=n; i+=2) print a[i] }' /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/JenkinsESP/data/plugs/plugsFailure.txt
+ cp /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/JenkinsESP/data/plugs/plugsIgnore.txt .
+ set +x
Testing CSM files:
data/Plugs/plugs0a.csm
data/Plugs/plugs0b.csm
data/Plugs/plugs0c.csm
data/Plugs/plugs0d.csm
total 42288
-rw-r-----  1 jenkins  staff   1.2M Jul 16 08:45 ASTRO.D01
-rw-r-----  1 jenkins  staff   277K Jul 16 08:45 ASTRO.IDX
-rwxr-xr-x  1 jenkins  staff   132K Jul 16 08:46 ESPxddm
-rwxr-xr-x  1 jenkins  staff   198K Jul 16 08:46 Slugs
-rwxr-xr-x  1 jenkins  staff    86K Jul 16 08:46 TestFit
-rwxr-xr-x  1 jenkins  staff   1.6M Jul 16 08:45 avl
-rwxr-xr-x  1 jenkins  staff    51K Jul 16 08:46 cart3dTest
-rwxr-xr-x  1 jenkins  staff    51K Jul 16 08:46 egads2cart
-rwxr-xr-x  1 jenkins  staff   307K Jul 16 08:45 friction
-rwxr-xr-x  1 jenkins  staff    10M Jul 16 08:45 mastros.exe
-rwxr-xr-x  1 jenkins  staff   749K Jul 16 08:45 mses
-rwxr-xr-x  1 jenkins  staff   1.4M Jul 16 08:45 mset
-rwxr-xr-x  1 jenkins  staff    51K Jul 16 08:46 phaseUtil
-rw-r--r--  1 jenkins  staff   1.5K Jul 16 12:17 pod.egads
-rw-r--r--  1 jenkins  staff     0B Jul 16 12:17 port7681.jrnl
-rwxr-xr-x  1 jenkins  staff   491K Jul 16 08:45 pplot
-rwxr-xr-x  1 jenkins  staff   450K Jul 16 08:45 pxplot
-rwxr-xr-x  1 jenkins  staff    69K Jul 16 08:46 sensCSM
-rwxr-xr-x  1 jenkins  staff   193K Jul 16 08:46 serveCSM
-rwxr-xr-x  1 jenkins  staff   159K Jul 16 08:46 serveESP
-rwxr-xr-x  1 jenkins  staff    52K Jul 16 08:46 vCurvature
-rwxr-xr-x  1 jenkins  staff    51K Jul 16 08:46 vGeom
-rwxr-xr-x  1 jenkins  staff    53K Jul 16 08:46 vTess
-rwxr-xr-x  1 jenkins  staff   1.8M Jul 16 08:46 vTesstatic
-rw-r--r--  1 jenkins  staff   195K Jul 16 12:17 wingMultiModel.bdf
-rwxr-xr-x  1 jenkins  staff   1.1M Jul 16 08:45 xfoil
( 1 / 4 )
data/Plugs/plugs0a.csm;
++ /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/bin/serveCSM -outLevel 0 -plugs 25 -plot /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/plugs0.cloud -batch -verify -jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/buildFinal.jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/plugs0a.csm
WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/verify_7.6.0/plugs0a.vfy", so verification is being skipped

===================================
PLUGS with 4562 points in the cloud
===================================


PLUGS phase1: match bounding boxes


PLUGS phase2: match cloud points
Starting pass 1 (of 25) of phase2
    Pass  1 converged, dmax= 5.416e-07,     rmsbest= 6.132e-04, reclass= 4562, unclass=    0
Starting pass 2 (of 25) of phase2
    Pass  2 converged, dmax= 5.366e-07,     rmsbest= 7.097e-04, reclass=    2, unclass=    0
Starting pass 3 (of 25) of phase2

    Phase2 passes converged because points are classified same as previous pass


==> Opening input journal file "/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/buildFinal.jrnl"


==> Closing input journal file

==> serveCSM completed successfully with no verification data

real	0m4.268s
user	0m4.419s
sys	0m0.237s
++ set +x
data/Plugs/plugs0a                  passed (as expected)
--------------------------------------------------------------------------------------------------
( 2 / 4 )
data/Plugs/plugs0b.csm;
++ /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/bin/serveCSM -outLevel 0 -plugs 25 -plot /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/plugs0.cloud -batch -verify -jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/buildFinal.jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/plugs0b.csm
WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/verify_7.6.0/plugs0b.vfy", so verification is being skipped

===================================
PLUGS with 4562 points in the cloud
===================================


PLUGS phase1: match bounding boxes


PLUGS phase2: match cloud points
Starting pass 1 (of 25) of phase2
    Pass  1 converged, dmax= 3.039e-07,     rmsbest= 4.036e-02, reclass= 4562, unclass=    0
Starting pass 2 (of 25) of phase2
    Pass  2 converged, dmax= 2.814e-07,     rmsbest= 1.924e-03, reclass= 1033, unclass=    0
Starting pass 3 (of 25) of phase2
    Pass  3 converged, dmax= 4.494e-07,     rmsbest= 5.920e-04, reclass=  473, unclass=    0
Starting pass 4 (of 25) of phase2
    Pass  4 converged, dmax= 5.366e-07,     rmsbest= 7.097e-04, reclass=   17, unclass=    0
Starting pass 5 (of 25) of phase2

    Phase2 passes converged because points are classified same as previous pass


==> Opening input journal file "/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/buildFinal.jrnl"


==> Closing input journal file

==> serveCSM completed successfully with no verification data

real	0m4.047s
user	0m5.059s
sys	0m0.020s
++ set +x
data/Plugs/plugs0b                  passed (as expected)
--------------------------------------------------------------------------------------------------
( 3 / 4 )
data/Plugs/plugs0c.csm;
++ /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/bin/serveCSM -outLevel 0 -plugs 25 -plot /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/plugs0.cloud -batch -verify -jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/buildFinal.jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/plugs0c.csm
WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/verify_7.6.0/plugs0c.vfy", so verification is being skipped

===================================
PLUGS with 4562 points in the cloud
===================================


PLUGS phase1: match bounding boxes


PLUGS phase2: match cloud points
Starting pass 1 (of 25) of phase2
    Pass  1 ran out of iterations,          rmsbest= 1.677e-01, reclass= 4562, unclass=  554
Starting pass 2 (of 25) of phase2
    Pass  2 converged, dmax= 4.016e-07,     rmsbest= 6.330e-02, reclass= 1676, unclass=    0
Starting pass 3 (of 25) of phase2
    Pass  3 converged, dmax= 1.881e-07,     rmsbest= 8.736e-03, reclass=  791, unclass=    0
Starting pass 4 (of 25) of phase2
    Pass  4 converged, dmax= 3.081e-07,     rmsbest= 1.037e-03, reclass=  428, unclass=    0
Starting pass 5 (of 25) of phase2
    Pass  5 converged, dmax= 5.816e-07,     rmsbest= 7.097e-04, reclass=  109, unclass=    0
Starting pass 6 (of 25) of phase2

    Phase2 passes converged because points are classified same as previous pass


==> Opening input journal file "/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/buildFinal.jrnl"


==> Closing input journal file

==> serveCSM completed successfully with no verification data

real	0m13.109s
user	0m20.882s
sys	0m0.042s
++ set +x
data/Plugs/plugs0c                  passed (as expected)
--------------------------------------------------------------------------------------------------
( 4 / 4 )
data/Plugs/plugs0d.csm;
++ /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/bin/serveCSM -outLevel 0 -plugs 25 -plot /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/plugs0.cloud -batch -verify -jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/buildFinal.jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/plugs0d.csm
WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/verify_7.6.0/plugs0d.vfy", so verification is being skipped

===================================
PLUGS with 4562 points in the cloud
===================================


PLUGS phase1: match bounding boxes


PLUGS phase2: match cloud points
Starting pass 1 (of 25) of phase2
    Pass  1 ran out of iterations,          rmsbest= 1.677e-01, reclass= 4562, unclass=  554
Starting pass 2 (of 25) of phase2
    Pass  2 converged, dmax= 4.016e-07,     rmsbest= 6.330e-02, reclass= 1676, unclass=    0
Starting pass 3 (of 25) of phase2
    Pass  3 converged, dmax= 1.881e-07,     rmsbest= 8.736e-03, reclass=  791, unclass=    0
Starting pass 4 (of 25) of phase2
    Pass  4 converged, dmax= 3.081e-07,     rmsbest= 1.037e-03, reclass=  428, unclass=    0
Starting pass 5 (of 25) of phase2
    Pass  5 converged, dmax= 5.816e-07,     rmsbest= 7.097e-04, reclass=  109, unclass=    0
Starting pass 6 (of 25) of phase2

    Phase2 passes converged because points are classified same as previous pass


==> Opening input journal file "/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen/ESP121/EngSketchPad/data/Plugs/buildFinal.jrnl"


==> Closing input journal file

==> serveCSM completed successfully with no verification data

real	0m13.047s
user	0m20.762s
sys	0m0.043s
++ set +x
data/Plugs/plugs0d                  passed (as expected)
--------------------------------------------------------------------------------------------------
[Execution node] check if [viggen] 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: '/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen')
[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: '/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_bPreBuilt/ESPVersion/121/buildnode/viggen')
[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 (121,viggen)
[Static Analysis] Using reference build 'ESP_bPreBuilt/ESPVersion=121,buildnode=viggen #36' 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_bPreBuilt/ESPVersion=121,buildnode=viggen #37'.
[Checks API] No suitable checks publisher found.
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] Deferred wipeout is used...
[WS-CLEANUP] done
Finished: SUCCESS