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Compute the surface curvature.
Max K: 64.288. Mean K: 0.464342. Standard deviation K: 2.13452.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        2.00368|        81.0874|
|     CV Face Area Aspect Ratio|        1.46525|         528462|
|           CV Sub-Volume Ratio|              1|    3.66809e+07|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     11564|    1/1.00|        10|
|         1|      2057|    1/5.62|   8.43594|
|         2|       415|    1/4.96|   7.42157|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 24.3915 m.
Wetted area = 2151.66 m^2.
Area projection in the x-plane = 830.863 m^2, y-plane = 916.212 m^2, z-plane = 78.5019 m^2.
Max. coordinate in the x-direction = 2.37666 m, y-direction = 24.3915 m, z-direction = 0.603659 m.
Min. coordinate in the x-direction = -19.2916 m, y-direction = -0.226076 m, z-direction = -208.488 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is NOT 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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   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|  4.0438e-01|    7.324703|   10.291558|   10.325418|   12.793809|    0.075595|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  4.1905e-01|    7.892694|   10.387335|   10.341545|   13.310450|    0.074677|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  4.2580e-01|    7.986091|   10.441704|   10.343121|   13.400119|   -0.004865|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       7.98609|         < -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).
+-----------------------------------------------------------------------+
Warning: there are 480 non-physical points in the solution.
Warning: 53 reconstructed states for upwinding are non-physical.

--------------------------- Finalizing Solver ---------------------------
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 =  26.853765
Cd =  -5519.63933

real	1m22.604s
user	1m9.025s
sys	0m5.790s
+ 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_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64/ESP/DARWIN64/examples/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_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64/ESP/DARWIN64/examples/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
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.7
AFLR2    : Version Date   07/16/23 @ 01:42PM
AFLR2    : Compile OS     Darwin 22.5.0 x86_64
AFLR2    : Compile Date   07/25/23 @ 11:59AM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 11.5.9
AFLR4    : Version Date   08/14/23 @ 12:27AM
AFLR4    : Compile OS     Darwin 22.5.0 x86_64
AFLR4    : Compile Date   08/14/23 @ 01:13PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.25
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

EGADS    : EGADS CAD Geometry Setup

EGADS    : Model has 1 Active Bodies

EGADS    : Body 0 is a SolidBody
EGADS    : Body 0 has 1 Shells
EGADS    : Body 0 has 9 Faces
EGADS    : Body 0 has 18 Edges
EGADS    : Body 0 has 10 Loops
EGADS    : Body 0 has 12 Nodes

EGADS    : Check Grid BCs

EGADS    : Grid BCs are OK

EGADS    : Face Neighbor-Faces Information

EGADS    : QC  = Face Quad Combination Flag
EGADS    : IER = Face Isolated Edge Refinement Flag
EGADS    : ER  = Face Edge Refinement Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.
EGADS    : SF  = Face Scale Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.

EGADS    :   Face          Body    QC   IER       ER    Scale   Neighbor
EGADS    :     ID  Active    ID  Flag  Flag   Weight   Factor   Faces
EGADS    :      1     Yes     0     0     1        0        1   2 3 4 5
EGADS    :      2     Yes     0     0     1        0        1   1 3 5 6
EGADS    :      3     Yes     0     0     1        0        1   1 2 4 6 7 8
EGADS    :      4     Yes     0     0     1        0        1   1 3 5 6
EGADS    :      5     Yes     0     0     1        0        1   1 2 4 6
EGADS    :      6     Yes     0     0     1        0        1   2 3 4 5
EGADS    :      7     Yes     0     0     1        0        1   3 8 9
EGADS    :      8     Yes     0     0     1        0        1   3 7 9
EGADS    :      9     Yes     0     0     1        0        1   7 8

EGADS    : Face Edges Information

EGADS    :   Face   Edges
EGADS    :      1   1 2 -3 -4
EGADS    :      2   5 6 -7 -1
EGADS    :      3   -2 7 9 -8 -10 -11
EGADS    :      4   -12 3 8 -13
EGADS    :      5   4 12 -14 -5
EGADS    :      6   -6 14 13 -9
EGADS    :      7   15 10 -17 -16
EGADS    :      8   17 11 -15 -18
EGADS    :      9   16 18

EGADS    : Face Loops Information

EGADS    :   Face   Loops
EGADS    :      1   1
EGADS    :      2   2
EGADS    :      3   3 4
EGADS    :      4   5
EGADS    :      5   6
EGADS    :      6   7
EGADS    :      7   8
EGADS    :      8   9
EGADS    :      9   10

EGADS    : Loop Edges Information

EGADS    :   Loop  Active Sense   Edges
EGADS    :      1     Yes     1   1 2 -3 -4
EGADS    :      2     Yes     1   5 6 -7 -1
EGADS    :      3     Yes     1   -2 7 9 -8
EGADS    :      4     Yes     1   -10 -11
EGADS    :      5     Yes     1   -12 3 8 -13
EGADS    :      6     Yes     1   4 12 -14 -5
EGADS    :      7     Yes     1   -6 14 13 -9
EGADS    :      8     Yes     1   15 10 -17 -16
EGADS    :      9     Yes     1   17 11 -15 -18
EGADS    :     10     Yes     1   16 18

EGADS    : Edge Node, Scale Factor, and Neighbor-Faces Information

EGADS    : ESF = Edge Scale Factor
EGADS    :       Not applicable for DEGENERATE Edges or Edges with a FarField
EGADS    :       Grid BC Neighbor Face.

EGADS    :                                             Neighbor
EGADS    :   Edge  Body  Active Node1 Node2      ESF   Faces
EGADS    :      1     0     Yes     2     1        1   1 2
EGADS    :      2     0     Yes     1     3        1   1 3
EGADS    :      3     0     Yes     4     3        1   1 4
EGADS    :      4     0     Yes     2     4        1   1 5
EGADS    :      5     0     Yes     2     5        1   2 5
EGADS    :      6     0     Yes     5     6        1   2 6
EGADS    :      7     0     Yes     1     6        1   2 3
EGADS    :      8     0     Yes     3     7        1   3 4
EGADS    :      9     0     Yes     6     7        1   3 6
EGADS    :     10     0     Yes     8     9        1   3 7
EGADS    :     11     0     Yes     9     8        1   3 8
EGADS    :     12     0     Yes     4    10        1   4 5
EGADS    :     13     0     Yes    10     7        1   4 6
EGADS    :     14     0     Yes     5    10        1   5 6
EGADS    :     15     0     Yes    11     8        1   7 8
EGADS    :     16     0     Yes    11    12        1   7 9
EGADS    :     17     0     Yes    12     9        1   7 8
EGADS    :     18     0     Yes    12    11        1   8 9

EGADS    : Node Information

EGADS    :   Node  Active      Coordinates
EGADS    :      1     Yes                0                0                0
EGADS    :      2     Yes                0               40                0
EGADS    :      3     Yes                0                0               20
EGADS    :      4     Yes                0               40               20
EGADS    :      5     Yes               20               40                0
EGADS    :      6     Yes               20                0                0
EGADS    :      7     Yes               20                0               20
EGADS    :      8     Yes       1.61374306                0                0
EGADS    :      9     Yes                0                0                0
EGADS    :     10     Yes               20               40               20
EGADS    :     11     Yes       2.53650745       3.87298335      0.334116517
EGADS    :     12     Yes       1.57194608       3.87298335      0.249728332

EGADS    : Face and Edge Match Information

EGADS    : No Face Matches Found

AFLR4    : Surface Mesh Spacing Setup

AFLR4    : Max Bounding Box Length     = 40
AFLR4    : Min Bounding Box Length     = 40
AFLR4    : Max Ref Bounding Box Length = 40
AFLR4    : Min Ref Bounding Box Length = 40
AFLR4    : Reference Length            = 3.22749
AFLR4    : BL Thickness                = 0
AFLR4    : Abs Min Surf Spacing        = 0.00806872
AFLR4    : Min Surf Spacing            = 0.322749
AFLR4    : Max Surf Spacing            = 2.42061
AFLR4    : Global Scale Factor         = 1

AFLR4    : Geometry Definition Information

AFLR4    : Definition              Definition   Composite             Grid BC
AFLR4    :         ID                    Type          ID                Type
AFLR4    :          0     glue-only composite           -                   -
AFLR4    :          1            CAD geometry           0            STD w/BL
AFLR4    :          2            CAD geometry           0            STD w/BL
AFLR4    :          3            CAD geometry           0            STD w/BL
AFLR4    :          4            CAD geometry           0            STD w/BL
AFLR4    :          5            CAD geometry           0            STD w/BL
AFLR4    :          6            CAD geometry           0            STD w/BL
AFLR4    :          7            CAD geometry           0            STD w/BL
AFLR4    :          8            CAD geometry           0            STD w/BL
AFLR4    :          9            CAD geometry           0            STD w/BL

AFLR4    : Define CAD surface definition 1
AFLR4    : Define CAD surface definition 2
AFLR4    : Define CAD surface definition 3
AFLR4    : Define CAD surface definition 4
AFLR4    : Define CAD surface definition 5
AFLR4    : Define CAD surface definition 6
AFLR4    : Define CAD surface definition 7
AFLR4    : Define CAD surface definition 8
AFLR4    : Define CAD surface definition 9

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Trias,Quads=       376       682         0
AFLR4    : Nodes, Trias,Quads=       381       692         0

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Trias,Quads=       374       678         0
AFLR4    : Nodes, Trias,Quads=       380       690         0

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Trias,Quads=       984      1890         0
AFLR4    : Nodes, Trias,Quads=       852      1626         0

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Trias,Quads=       376       682         0
AFLR4    : Nodes, Trias,Quads=       380       690         0

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Trias,Quads=       374       678         0
AFLR4    : Nodes, Trias,Quads=       380       690         0

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Trias,Quads=       376       682         0
AFLR4    : Nodes, Trias,Quads=       378       686         0

AFLR4    : Generate optimal mesh on surface definition 7
AFLR2    : Nodes, Trias,Quads=        91       147         0
AFLR4    : Nodes, Trias,Quads=        72       109         0

AFLR4    : Generate optimal mesh on surface definition 8
AFLR2    : Nodes, Trias,Quads=        89       142         0
AFLR4    : Nodes, Trias,Quads=        70       104         0

AFLR4    : Generate optimal mesh on surface definition 9
AFLR2    : Nodes, Trias,Quads=        11        13         0
AFLR4    : Nodes, Trias,Quads=         7         5         0

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      2648      5292       492

AFLR4    : Curvature BG Surface Grid Generation

AFLR4    : Nodes, Faces      =      2648      5292

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Trias,Quads=       386       702         0
AFLR4    : Nodes, Trias,Quads=       379       688         0

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Trias,Quads=       383       696         0
AFLR4    : Nodes, Trias,Quads=       381       692         0

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Trias,Quads=      1073      2066         0
AFLR4    : Nodes, Trias,Quads=      1011      1942         0

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Trias,Quads=       383       696         0
AFLR4    : Nodes, Trias,Quads=       379       688         0

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Trias,Quads=       386       702         0
AFLR4    : Nodes, Trias,Quads=       382       694         0

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Trias,Quads=       382       694         0
AFLR4    : Nodes, Trias,Quads=       379       688         0

AFLR4    : Generate optimal mesh on surface definition 7
AFLR2    : Nodes, Trias,Quads=        99       160         0
AFLR4    : Nodes, Trias,Quads=        81       124         0

AFLR4    : Generate optimal mesh on surface definition 8
AFLR2    : Nodes, Trias,Quads=        96       154         0
AFLR4    : Nodes, Trias,Quads=        77       116         0

AFLR4    : Generate optimal mesh on surface definition 9
AFLR2    : Nodes, Trias,Quads=        11        12         0
AFLR4    : Nodes, Trias,Quads=         8         6         0

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      2821      5638       500

OVERALL  : CPU Time          =     0.300   seconds
Body 1 (of 1)
Number of nodes    = 2821
Number of elements = 5638
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 5638
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 2821
Total number of elements = 5638
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Farfield, index = 1
	Name = SymmPlane, index = 2
	Name = Skin, index = 3
Getting volume mesh
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.7
AFLR2    : Version Date   07/16/23 @ 01:42PM
AFLR2    : Compile OS     Darwin 22.5.0 x86_64
AFLR2    : Compile Date   07/25/23 @ 11:59AM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 11.5.9
AFLR4    : Version Date   08/14/23 @ 12:27AM
AFLR4    : Compile OS     Darwin 22.5.0 x86_64
AFLR4    : Compile Date   08/14/23 @ 01:13PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.25
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.25
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------
Volume mesh:
	Number of nodes          = 11564
	Number of elements       = 65500
	Number of triangles      = 5638
	Number of quadrilatarals = 0
	Number of tetrahedrals   = 59862
	Number of pyramids       = 0
	Number of prisms         = 0
	Number of hexahedrals    = 0
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 "Harrier (8.0.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   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 2012-2023, 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: ../aflr3/aflr3_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.
11564 grid points.
59862 volume elements.
3 surface markers.
3450 boundary elements in index 0 (Marker = BC_1).
1942 boundary elements in index 1 (Marker = BC_2).
246 boundary elements in index 2 (Marker = BC_3).
59862 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: 50.9602. Mean K: 0.84105. Standard deviation K: 3.91738.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        51.6918|        86.3913|
|     CV Face Area Aspect Ratio|        1.04466|        19.2647|
|           CV Sub-Volume Ratio|              1|        8.65233|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     11564|    1/1.00|        10|
|         1|      2057|    1/5.62|   8.43594|
|         2|       416|    1/4.94|   7.42753|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 8.34786 m^2.
Area projection in the x-plane = 0.588155 m^2, y-plane = 0.276999 m^2, z-plane = 3.94869 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380417 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.85958e-18 m, z-direction = -0.0467006 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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   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|  3.9991e-01|   -0.829249|    1.482443|    1.171374|    4.639857|   -1.038196|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  4.0941e-01|   -1.159834|    1.372574|    1.018520|    4.293619|   -0.652554|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  4.0922e-01|   -1.204489|    1.232482|    0.850876|    4.247694|    0.347942|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.20449|         < -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).
+-----------------------------------------------------------------------+

--------------------------- Finalizing Solver ---------------------------
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 capsReference attributes ................
	Number of unique capsReference 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
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 746
	Number of elements = 898
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 120
	Elemental Quad4 = 778
Aero_Reference value is NULL - No aero reference parameters set

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
Optimization Control tuple is NULL - Default optimization control is used

Getting FEA optimization control.......
Done getting FEA Optimization Control
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 = 16
	Number of data points = 130
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 3.095428e+09, tgt = 3.095428e+09, diff = 9.834136e+01
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 16
	Number of data points = 130
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 3.012963e+09, tgt = 3.012963e+09, diff = 7.230747e+01
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 16
	Number of data points = 130
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 4.096833e+07, tgt = 4.096833e+07, diff = 2.694621e+00
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 330 (total = 330)
Extracting external pressure loads from data transfer....
	TransferName = Skin_Bottom
	Number of Elements = 330 (total = 660)
Extracting external pressure loads from data transfer....
	TransferName = Skin_Tip
	Number of Elements = 30 (total = 690)

Writing Astros grid and connectivity file (in free 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 IEEE_DENORMAL
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 "Harrier (8.0.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2023, 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: ../aflr3/aflr3_0.su2

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


-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: ../aflr3/aflr3_0.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.
11564 grid points.
59862 volume elements.
3 surface markers.
3450 boundary elements in index 0 (Marker = BC_1).
1942 boundary elements in index 1 (Marker = BC_2).
246 boundary elements in index 2 (Marker = BC_3).
59862 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).


Completed in 2.049684 seconds on 1 core.

----------------------- Write deformed grid files -----------------------
|SU2 mesh                           |../aflr3/aflr3_0.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.

------------------------- Finalize Solver -------------------------
Deleted CNumerics container.
Deleted CSolver container.
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

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


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   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 2012-2023, 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: ../aflr3/aflr3_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.
11564 grid points.
59862 volume elements.
3 surface markers.
3450 boundary elements in index 0 (Marker = BC_1).
1942 boundary elements in index 1 (Marker = BC_2).
246 boundary elements in index 2 (Marker = BC_3).
59862 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 25257 TETRAHEDRON volume elements.
There has been a re-orientation of 1510 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 592743.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 144.553. Mean K: 1.75261. Standard deviation K: 9.41741.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|       0.681138|        82.9995|
|     CV Face Area Aspect Ratio|        1.44721|        558.927|
|           CV Sub-Volume Ratio|              1|        94569.6|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     11564|    1/1.00|        10|
|         1|      2051|    1/5.64|   8.42773|
|         2|       417|    1/4.92|   7.43347|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 26.614 m.
Wetted area = 3533.23 m^2.
Area projection in the x-plane = 622.752 m^2, y-plane = 1111.96 m^2, z-plane = 118.544 m^2.
Max. coordinate in the x-direction = 5.24163 m, y-direction = 26.614 m, z-direction = 26.1448 m.
Min. coordinate in the x-direction = -12.7968 m, y-direction = -0.879728 m, z-direction = -281.754 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is NOT 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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   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|  4.1904e-01|    3.693433|    6.658657|    6.818857|    9.162539|   -0.372005|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  4.0050e-01|    4.024253|    6.536197|    6.672442|    9.358028|   -0.305008|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  4.0398e-01|    4.561360|    7.524451|    6.684152|   10.266171|   -0.226932|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       4.56136|         < -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).
+-----------------------------------------------------------------------+
Warning: there are 386 non-physical points in the solution.
Warning: 5 reconstructed states for upwinding are non-physical.

--------------------------- Finalizing Solver ---------------------------
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 = 16
	Number of data points = 130
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 9.582794e+08, tgt = 9.582793e+08, diff = 9.226755e+01
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 16
	Number of data points = 130
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 8.198964e+08, tgt = 8.198966e+08, diff = 1.837985e+02
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 16
	Number of data points = 130
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 1.066088e+07, tgt = 1.066091e+07, diff = 2.495453e+01
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 330 (total = 330)
Extracting external pressure loads from data transfer....
	TransferName = Skin_Bottom
	Number of Elements = 330 (total = 660)
Extracting external pressure loads from data transfer....
	TransferName = Skin_Tip
	Number of Elements = 30 (total = 690)

Writing Astros grid and connectivity file (in free 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 IEEE_DENORMAL
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 "Harrier (8.0.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2023, 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: ../aflr3/aflr3_0.su2

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


-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: ../aflr3/aflr3_0.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.
11564 grid points.
59862 volume elements.
3 surface markers.
3450 boundary elements in index 0 (Marker = BC_1).
1942 boundary elements in index 1 (Marker = BC_2).
246 boundary elements in index 2 (Marker = BC_3).
59862 tetrahedra.

----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
There has been a re-orientation of 25257 TETRAHEDRON volume elements.
There has been a re-orientation of 1510 TRIANGLE surface elements.
Identify edges and vertices.
Setting the bound control volume structure.
Volume of the computational grid: 592743.
  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).


Completed in 37.441431 seconds on 1 core.

----------------------- Write deformed grid files -----------------------
|SU2 mesh                           |../aflr3/aflr3_0.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.

------------------------- Finalize Solver -------------------------
Deleted CNumerics container.
Deleted CSolver container.
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

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


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   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 2012-2023, 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: ../aflr3/aflr3_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.
11564 grid points.
59862 volume elements.
3 surface markers.
3450 boundary elements in index 0 (Marker = BC_1).
1942 boundary elements in index 1 (Marker = BC_2).
246 boundary elements in index 2 (Marker = BC_3).
59862 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 36673 TETRAHEDRON volume elements.
There has been a re-orientation of 1508 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 5.25064e+10.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 7.86228. Mean K: 0.265315. Standard deviation K: 0.815464.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        2.09971|        81.9941|
|     CV Face Area Aspect Ratio|        1.42935|        32503.1|
|           CV Sub-Volume Ratio|              1|    2.51478e+06|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     11564|    1/1.00|        10|
|         1|      2065|     1/5.6|   8.44686|
|         2|       422|    1/4.89|   7.46307|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 8.14288 m.
Wetted area = 332194 m^2.
Area projection in the x-plane = 73574.9 m^2, y-plane = 135782 m^2, z-plane = 9173.42 m^2.
Max. coordinate in the x-direction = 35.2535 m, y-direction = 8.14288 m, z-direction = 3533.55 m.
Min. coordinate in the x-direction = -25.167 m, y-direction = -256.304 m, z-direction = -0.0467006 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is NOT 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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   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|  4.1861e-01|    6.654037|    9.621028|    9.600169|   12.123143|   -0.046783|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  4.3075e-01|    7.142188|    9.680721|    9.601090|   12.523565|   -0.046448|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  4.3010e-01|    7.290828|    9.814668|    9.685370|   12.622466|   -0.046733|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       7.29083|         < -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).
+-----------------------------------------------------------------------+
Warning: there are 518 non-physical points in the solution.
Warning: 64 reconstructed states for upwinding are non-physical.

--------------------------- Finalizing Solver ---------------------------
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 = 16
	Number of data points = 130
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
            Rank 0: src = 1.346834e+09, tgt = 1.346833e+09, diff = 4.009710e+02
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 16
	Number of data points = 130
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
            Rank 0: src = 1.260077e+09, tgt = 1.260077e+09, diff = 7.112548e+01
Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv
	Number of variables = 16
	Number of data points = 130
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
            Rank 0: src = 1.663708e+07, tgt = 1.663713e+07, diff = 4.494275e+01
Extracting external pressure loads from data transfer....
	TransferName = Skin_Top
	Number of Elements = 330 (total = 330)
Extracting external pressure loads from data transfer....
	TransferName = Skin_Bottom
	Number of Elements = 330 (total = 660)
Extracting external pressure loads from data transfer....
	TransferName = Skin_Tip
	Number of Elements = 30 (total = 690)

Writing Astros grid and connectivity file (in free 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 IEEE_DENORMAL
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 "Harrier (8.0.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2023, 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: ../aflr3/aflr3_0.su2

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


-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: ../aflr3/aflr3_0.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.
11564 grid points.
59862 volume elements.
3 surface markers.
3450 boundary elements in index 0 (Marker = BC_1).
1942 boundary elements in index 1 (Marker = BC_2).
246 boundary elements in index 2 (Marker = BC_3).
59862 tetrahedra.

----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
There has been a re-orientation of 36673 TETRAHEDRON volume elements.
There has been a re-orientation of 1508 TRIANGLE surface elements.
Identify edges and vertices.
Setting the bound control volume structure.
Volume of the computational grid: 5.25064e+10.
  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).


Completed in 37.343990 seconds on 1 core.

----------------------- Write deformed grid files -----------------------
|SU2 mesh                           |../aflr3/aflr3_0.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.

------------------------- Finalize Solver -------------------------
Deleted CNumerics container.
Deleted CSolver container.
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

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


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   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 2012-2023, 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: ../aflr3/aflr3_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.
11564 grid points.
59862 volume elements.
3 surface markers.
3450 boundary elements in index 0 (Marker = BC_1).
1942 boundary elements in index 1 (Marker = BC_2).
246 boundary elements in index 2 (Marker = BC_3).
59862 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 24328 TETRAHEDRON volume elements.
There has been a re-orientation of 2467 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 5.00926e+12.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 10.653. Mean K: 0.271833. Standard deviation K: 1.01119.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|       0.950825|        81.5182|
|     CV Face Area Aspect Ratio|        1.55156|    2.83122e+06|
|           CV Sub-Volume Ratio|              1|      6.158e+07|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     11564|    1/1.00|        10|
|         1|      2056|    1/5.62|   8.43457|
|         2|       413|    1/4.98|   7.40963|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 4.00725 m.
Wetted area = 83355.6 m^2.
Area projection in the x-plane = 4556.49 m^2, y-plane = 38472.1 m^2, z-plane = 2401.06 m^2.
Max. coordinate in the x-direction = 13.9634 m, y-direction = 4.00725 m, z-direction = 1611.15 m.
Min. coordinate in the x-direction = -11.0923 m, y-direction = -113.219 m, z-direction = -21.6037 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_3 is NOT a single plane.
Boundary marker BC_2 is NOT 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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   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|  4.3533e-01|    8.011600|   10.978455|   11.018605|   13.480706|   -0.036624|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  4.3940e-01|    8.490791|   11.030665|   11.046346|   13.887386|   -0.034950|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  4.3947e-01|    8.628748|   11.116510|   11.128731|   13.976825|   -0.035146|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       8.62875|         < -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).
+-----------------------------------------------------------------------+
Warning: there are 943 non-physical points in the solution.
Warning: 51 reconstructed states for upwinding are non-physical.

--------------------------- Finalizing Solver ---------------------------
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	3m11.999s
user	2m58.369s
sys	0m11.968s
+ status=0
+ set +x

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


=================================================
+ echo 'aeroelasticSimple_Temperature_SU2_and_TACS.py test;'
+ tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt
aeroelasticSimple_Temperature_SU2_and_TACS.py test;
+ python -u aeroelasticSimple_Temperature_SU2_and_TACS.py -outLevel=0 -noPlotData
+ tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64/ESP/DARWIN64/examples/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
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.7
AFLR2    : Version Date   07/16/23 @ 01:42PM
AFLR2    : Compile OS     Darwin 22.5.0 x86_64
AFLR2    : Compile Date   07/25/23 @ 11:59AM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 11.5.9
AFLR4    : Version Date   08/14/23 @ 12:27AM
AFLR4    : Compile OS     Darwin 22.5.0 x86_64
AFLR4    : Compile Date   08/14/23 @ 01:13PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.25
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

EGADS    : EGADS CAD Geometry Setup

EGADS    : Model has 1 Active Bodies

EGADS    : Body 0 is a SolidBody
EGADS    : Body 0 has 1 Shells
EGADS    : Body 0 has 9 Faces
EGADS    : Body 0 has 18 Edges
EGADS    : Body 0 has 10 Loops
EGADS    : Body 0 has 12 Nodes

EGADS    : Check Grid BCs

EGADS    : Grid BCs are OK

EGADS    : Face Neighbor-Faces Information

EGADS    : QC  = Face Quad Combination Flag
EGADS    : IER = Face Isolated Edge Refinement Flag
EGADS    : ER  = Face Edge Refinement Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.
EGADS    : SF  = Face Scale Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.

EGADS    :   Face          Body    QC   IER       ER    Scale   Neighbor
EGADS    :     ID  Active    ID  Flag  Flag   Weight   Factor   Faces
EGADS    :      1     Yes     0     0     1        0        1   2 3 4 5
EGADS    :      2     Yes     0     0     1        0        1   1 3 5 6
EGADS    :      3     Yes     0     0     1        0        1   1 2 4 6 7 8
EGADS    :      4     Yes     0     0     1        0        1   1 3 5 6
EGADS    :      5     Yes     0     0     1        0        1   1 2 4 6
EGADS    :      6     Yes     0     0     1        0        1   2 3 4 5
EGADS    :      7     Yes     0     0     1        0        1   3 8 9
EGADS    :      8     Yes     0     0     1        0        1   3 7 9
EGADS    :      9     Yes     0     0     1        0        1   7 8

EGADS    : Face Edges Information

EGADS    :   Face   Edges
EGADS    :      1   1 2 -3 -4
EGADS    :      2   5 6 -7 -1
EGADS    :      3   -2 7 9 -8 -10 -11
EGADS    :      4   -12 3 8 -13
EGADS    :      5   4 12 -14 -5
EGADS    :      6   -6 14 13 -9
EGADS    :      7   15 10 -17 -16
EGADS    :      8   17 11 -15 -18
EGADS    :      9   16 18

EGADS    : Face Loops Information

EGADS    :   Face   Loops
EGADS    :      1   1
EGADS    :      2   2
EGADS    :      3   3 4
EGADS    :      4   5
EGADS    :      5   6
EGADS    :      6   7
EGADS    :      7   8
EGADS    :      8   9
EGADS    :      9   10

EGADS    : Loop Edges Information

EGADS    :   Loop  Active Sense   Edges
EGADS    :      1     Yes     1   1 2 -3 -4
EGADS    :      2     Yes     1   5 6 -7 -1
EGADS    :      3     Yes     1   -2 7 9 -8
EGADS    :      4     Yes     1   -10 -11
EGADS    :      5     Yes     1   -12 3 8 -13
EGADS    :      6     Yes     1   4 12 -14 -5
EGADS    :      7     Yes     1   -6 14 13 -9
EGADS    :      8     Yes     1   15 10 -17 -16
EGADS    :      9     Yes     1   17 11 -15 -18
EGADS    :     10     Yes     1   16 18

EGADS    : Edge Node, Scale Factor, and Neighbor-Faces Information

EGADS    : ESF = Edge Scale Factor
EGADS    :       Not applicable for DEGENERATE Edges or Edges with a FarField
EGADS    :       Grid BC Neighbor Face.

EGADS    :                                             Neighbor
EGADS    :   Edge  Body  Active Node1 Node2      ESF   Faces
EGADS    :      1     0     Yes     2     1        1   1 2
EGADS    :      2     0     Yes     1     3        1   1 3
EGADS    :      3     0     Yes     4     3        1   1 4
EGADS    :      4     0     Yes     2     4        1   1 5
EGADS    :      5     0     Yes     2     5        1   2 5
EGADS    :      6     0     Yes     5     6        1   2 6
EGADS    :      7     0     Yes     1     6        1   2 3
EGADS    :      8     0     Yes     3     7        1   3 4
EGADS    :      9     0     Yes     6     7        1   3 6
EGADS    :     10     0     Yes     8     9        1   3 7
EGADS    :     11     0     Yes     9     8        1   3 8
EGADS    :     12     0     Yes     4    10        1   4 5
EGADS    :     13     0     Yes    10     7        1   4 6
EGADS    :     14     0     Yes     5    10        1   5 6
EGADS    :     15     0     Yes    11     8        1   7 8
EGADS    :     16     0     Yes    11    12        1   7 9
EGADS    :     17     0     Yes    12     9        1   7 8
EGADS    :     18     0     Yes    12    11        1   8 9

EGADS    : Node Information

EGADS    :   Node  Active      Coordinates
EGADS    :      1     Yes                0                0                0
EGADS    :      2     Yes                0               40                0
EGADS    :      3     Yes                0                0               20
EGADS    :      4     Yes                0               40               20
EGADS    :      5     Yes               20               40                0
EGADS    :      6     Yes               20                0                0
EGADS    :      7     Yes               20                0               20
EGADS    :      8     Yes       1.61374306                0                0
EGADS    :      9     Yes                0                0                0
EGADS    :     10     Yes               20               40               20
EGADS    :     11     Yes       2.53650745       3.87298335      0.334116517
EGADS    :     12     Yes       1.57194608       3.87298335      0.249728332

EGADS    : Face and Edge Match Information

EGADS    : No Face Matches Found

AFLR4    : Surface Mesh Spacing Setup

AFLR4    : Max Bounding Box Length     = 40
AFLR4    : Min Bounding Box Length     = 40
AFLR4    : Max Ref Bounding Box Length = 40
AFLR4    : Min Ref Bounding Box Length = 40
AFLR4    : Reference Length            = 1.61374
AFLR4    : BL Thickness                = 0
AFLR4    : Abs Min Surf Spacing        = 0.00403436
AFLR4    : Min Surf Spacing            = 0.161374
AFLR4    : Max Surf Spacing            = 1.21031
AFLR4    : Global Scale Factor         = 1

AFLR4    : Geometry Definition Information

AFLR4    : Definition              Definition   Composite             Grid BC
AFLR4    :         ID                    Type          ID                Type
AFLR4    :          0     glue-only composite           -                   -
AFLR4    :          1            CAD geometry           0            STD w/BL
AFLR4    :          2            CAD geometry           0            STD w/BL
AFLR4    :          3            CAD geometry           0            STD w/BL
AFLR4    :          4            CAD geometry           0            STD w/BL
AFLR4    :          5            CAD geometry           0            STD w/BL
AFLR4    :          6            CAD geometry           0            STD w/BL
AFLR4    :          7            CAD geometry           0            STD w/BL
AFLR4    :          8            CAD geometry           0            STD w/BL
AFLR4    :          9            CAD geometry           0            STD w/BL

AFLR4    : Define CAD surface definition 1
AFLR4    : Define CAD surface definition 2
AFLR4    : Define CAD surface definition 3
AFLR4    : Define CAD surface definition 4
AFLR4    : Define CAD surface definition 5
AFLR4    : Define CAD surface definition 6
AFLR4    : Define CAD surface definition 7
AFLR4    : Define CAD surface definition 8
AFLR4    : Define CAD surface definition 9

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Trias,Quads=      1318      2502         0
AFLR4    : Nodes, Trias,Quads=      1293      2452         0

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Trias,Quads=      1318      2502         0
AFLR4    : Nodes, Trias,Quads=      1298      2462         0

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Trias,Quads=      3418      6687         0
AFLR4    : Nodes, Trias,Quads=      3008      5867         0

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Trias,Quads=      1315      2496         0
AFLR4    : Nodes, Trias,Quads=      1297      2460         0

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Trias,Quads=      1318      2502         0
AFLR4    : Nodes, Trias,Quads=      1298      2462         0

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Trias,Quads=      1319      2504         0
AFLR4    : Nodes, Trias,Quads=      1294      2454         0

AFLR4    : Generate optimal mesh on surface definition 7
AFLR2    : Nodes, Trias,Quads=       200       344         0
AFLR4    : Nodes, Trias,Quads=       160       264         0

AFLR4    : Generate optimal mesh on surface definition 8
AFLR2    : Nodes, Trias,Quads=       193       330         0
AFLR4    : Nodes, Trias,Quads=       155       254         0

AFLR4    : Generate optimal mesh on surface definition 9
AFLR2    : Nodes, Trias,Quads=        17        21         0
AFLR4    : Nodes, Trias,Quads=        11         9         0

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      9344     18684       928

AFLR4    : Curvature BG Surface Grid Generation

AFLR4    : Nodes, Faces      =      9344     18684

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Trias,Quads=      1335      2536         0
AFLR4    : Nodes, Trias,Quads=      1317      2500         0

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Trias,Quads=      1337      2540         0
AFLR4    : Nodes, Trias,Quads=      1320      2506         0

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Trias,Quads=      3787      7420         0
AFLR4    : Nodes, Trias,Quads=      2943      5732         0

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Trias,Quads=      1341      2548         0
AFLR4    : Nodes, Trias,Quads=      1321      2508         0

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Trias,Quads=      1337      2540         0
AFLR4    : Nodes, Trias,Quads=      1320      2506         0

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Trias,Quads=      1342      2550         0
AFLR4    : Nodes, Trias,Quads=      1318      2502         0

AFLR4    : Generate optimal mesh on surface definition 7
AFLR2    : Nodes, Trias,Quads=       233       404         0
AFLR4    : Nodes, Trias,Quads=       210       358         0

AFLR4    : Generate optimal mesh on surface definition 8
AFLR2    : Nodes, Trias,Quads=       224       386         0
AFLR4    : Nodes, Trias,Quads=       196       330         0

AFLR4    : Generate optimal mesh on surface definition 9
AFLR2    : Nodes, Trias,Quads=        18        22         0
AFLR4    : Nodes, Trias,Quads=        12        10         0

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      9478     18952       946

OVERALL  : CPU Time          =     0.998   seconds
Body 1 (of 1)
Number of nodes    = 9478
Number of elements = 18952
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 18952
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 9478
Total number of elements = 18952
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Farfield, index = 1
	Name = SymmPlane, index = 2
	Name = Skin, index = 3
Getting volume mesh
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.7
AFLR2    : Version Date   07/16/23 @ 01:42PM
AFLR2    : Compile OS     Darwin 22.5.0 x86_64
AFLR2    : Compile Date   07/25/23 @ 11:59AM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 11.5.9
AFLR4    : Version Date   08/14/23 @ 12:27AM
AFLR4    : Compile OS     Darwin 22.5.0 x86_64
AFLR4    : Compile Date   08/14/23 @ 01:13PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.25
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.25
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------
Volume mesh:
	Number of nodes          = 61021
	Number of elements       = 351564
	Number of triangles      = 18952
	Number of quadrilatarals = 0
	Number of tetrahedrals   = 332612
	Number of pyramids       = 0
	Number of prisms         = 0
	Number of hexahedrals    = 0
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
Info: No recognized data transfer names found.
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.5.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   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 2012-2023, 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: ../aflr3/aflr3_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_Temperature_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Temperature_SM.
Volume file name: flow_aeroelasticSimple_Temperature_SM.
Restart file name: restart_flow_aeroelasticSimple_Temperature_SM.dat.

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

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

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

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

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
61021 grid points.
332612 volume elements.
3 surface markers.
12522 boundary elements in index 0 (Marker = BC_1).
5732 boundary elements in index 1 (Marker = BC_2).
698 boundary elements in index 2 (Marker = BC_3).
332612 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: 83.4538. Mean K: 0.863308. Standard deviation K: 5.00657.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        52.4071|        86.6424|
|     CV Face Area Aspect Ratio|        1.04128|        21.5651|
|           CV Sub-Volume Ratio|              1|        10.4254|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     61021|    1/1.00|        10|
|         1|     10400|    1/5.87|   8.31654|
|         2|      1824|     1/5.7|   6.98282|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 9.2451 m^2.
Area projection in the x-plane = 0.651846 m^2, y-plane = 0.30478 m^2, z-plane = 4.4157 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.38 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.86329e-18 m, z-direction = -0.0467611 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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  2.0202e+00|   -1.358658|    0.921673|    0.583457|    4.110448|   -0.914331|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  2.1100e+00|   -1.761379|    0.764232|    0.408273|    3.694369|   -0.434651|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  2.1259e+00|   -1.765424|    0.580434|    0.226849|    3.691843|    1.933305|

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

Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.76542|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticSimple_Temperature_SM.dat|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Temperature_SM.dat).
|CSV file                           |surface_flow_aeroelasticSimple_Temperature_SM.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Temperature_SM.dat).
|Tecplot binary                     |flow_aeroelasticSimple_Temperature_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Temperature_SM.dat).
|Tecplot binary surface             |surface_flow_aeroelasticSimple_Temperature_SM.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Temperature_SM.dat).
+-----------------------------------------------------------------------+

--------------------------- Finalizing Solver ---------------------------
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 ...... tacs
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Skin, index = 1
	Name = Rib_Root, index = 2
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 0
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 12
Number of elements = 12
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 4
Number of quadrilateral elements = 8
----------------------------
Total number of nodes    = 12
Total number of elements = 12
Mapping Csys attributes ................
	Number of unique Csys attributes = 0

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

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

Getting FEA properties.......
	Number of properties - 2
	Property name - Rib_Root
	Property name - Skin
	Done getting FEA properties
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 - Skin
	No "groupName" specified for Load tuple Skin, 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
Design_Equation tuple is NULL - No design equations applied
Design_Table tuple is NULL - No design table constants applied
Design_Opt_Param tuple is NULL - No design optimization parameters applied
Design_Response tuple is NULL - No design responses applied
Design_Equation_Response tuple is NULL - No design equation responses applied
Analysis tuple is NULL

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Default
	Done getting FEA analyses
Mapping Csys attributes ................
	Number of unique Csys attributes = 0

Getting FEA coordinate systems.......
	Number of coordinate systems - 0
	No coordinate systems found - defaulting to global
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = Rib_Root, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 1
	Name = Skin, index = 1
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 3
	Name = Skin_Top, index = 1
	Name = Skin_Bottom, index = 2
	Name = Skin_Tip, index = 3
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Skin, index = 1
	Name = Rib_Root, index = 2
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 12
	Number of elements = 12
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 4
	Elemental Quad4 = 8
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Temperature_SM.csv
	Number of variables = 16
	Number of data points = 361
 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Temperature'
            Rank 0: src = 1.497162e+03, tgt = 1.497162e+03, diff = 1.197986e-05
Mapping Csys attributes ................
	Number of unique Csys attributes = 0

Getting FEA coordinate systems.......
	Number of coordinate systems - 0
	No coordinate systems found - defaulting to global
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = Rib_Root, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 1
	Name = Skin, index = 1
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 3
	Name = Skin_Top, index = 1
	Name = Skin_Bottom, index = 2
	Name = Skin_Tip, index = 3
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Skin, index = 1
	Name = Rib_Root, index = 2
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 12
	Number of elements = 12
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 4
	Elemental Quad4 = 8
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Temperature_SM.csv
	Number of variables = 16
	Number of data points = 361
 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Temperature'
            Rank 0: src = 1.453298e+03, tgt = 1.453298e+03, diff = 2.126951e-06
Mapping Csys attributes ................
	Number of unique Csys attributes = 0

Getting FEA coordinate systems.......
	Number of coordinate systems - 0
	No coordinate systems found - defaulting to global
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = Rib_Root, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 1
	Name = Skin, index = 1
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 3
	Name = Skin_Top, index = 1
	Name = Skin_Bottom, index = 2
	Name = Skin_Tip, index = 3
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Skin, index = 1
	Name = Rib_Root, index = 2
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 12
	Number of elements = 12
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 4
	Elemental Quad4 = 8
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Temperature_SM.csv
	Number of variables = 16
	Number of data points = 361
 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Temperature'
            Rank 0: src = 2.097780e+01, tgt = 2.097780e+01, diff = 9.379164e-13
Extracting external thermal loads from data transfer....
	TransferName = Skin_Top
	Number of Nodes = 9 (total = 9)
Extracting external thermal loads from data transfer....
	TransferName = Skin_Bottom
	Number of Nodes = 9 (total = 18)
Extracting external thermal loads from data transfer....
	TransferName = Skin_Tip
	Number of Nodes = 4 (total = 16)

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

Writing subElement types (if any) - appending mesh file

Writing TACS instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint ADD cards
	Writing load cards
	Writing constraint cards
	Writing material cards
	Writing property cards

Running PostAnalysis ...... tacs

real	0m26.395s
user	0m22.895s
sys	0m2.507s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Temperature_SU2_and_TACS.py passed (as expected)
=================================================


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

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

Mystran
=================================================

All tests pass!


=================================================
=================================================
[GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64')
[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] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64')
[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_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64')
[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] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64')
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/DARWIN64')
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] No valid reference build found
[Static Analysis] All reported issues will be considered outstanding
[Static Analysis] No quality gates have been set - skipping
[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_MemcheckCaps/CASREV=7.6,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=DARWIN64,buildnode=macys #1362'.
[Checks API] No suitable checks publisher found.
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] done
Finished: SUCCESS