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 = 0.323 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR2 : Compile Date 07/25/23 @ 11:58AM
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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR4 : Compile Date 08/14/23 @ 01:20PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
Volume mesh:
Number of nodes = 11576
Number of elements = 65579
Number of triangles = 5638
Number of quadrilatarals = 0
Number of tetrahedrals = 59941
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 - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Harrier (8.0.0) "
Running SU2......
/home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/io/config.py:142: ResourceWarning: unclosed file <_io.TextIOWrapper name='aeroelasticSimple_Iterative_SM.cfg' mode='r' encoding='UTF-8'>
konfig = read_config(filename)
ResourceWarning: Enable tracemalloc to get the object allocation traceback
/home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/io/config.py:933: ResourceWarning: unclosed file <_io.TextIOWrapper name='config_CFD.cfg_tmp' mode='r' encoding='UTF-8'>
for raw_line in open(temp_filename):
ResourceWarning: Enable tracemalloc to get the object allocation traceback
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) 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_Iterative_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_SM.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_3|
+-----------------------------------------------------------------------+
| Far-field| BC_1|
+-----------------------------------------------------------------------+
| Symmetry plane| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
11576 grid points.
59941 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).
59941 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| 86.5125|
| CV Face Area Aspect Ratio| 1.13136| 19.2647|
| CV Sub-Volume Ratio| 1| 9.06145|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 11576| 1/1.00| 10|
| 1| 2051| 1/5.64| 8.42481|
| 2| 412| 1/4.98| 7.40109|
+-------------------------------------------+
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| 5.6836e-01| -0.829474| 1.482217| 1.171149| 4.639632| -1.102304|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.6935e-01| -1.157680| 1.366603| 1.021437| 4.295908| -0.718377|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.6230e-01| -1.203704| 1.222365| 0.849299| 4.248373| 0.350351|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.2037| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Iterative_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Iterative_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
+-----------------------------------------------------------------------+
--------------------------- 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) ------------------------
/home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/run/interface.py:114: ResourceWarning: unclosed file <_io.BufferedReader name=4>
run_command(the_Command)
ResourceWarning: Enable tracemalloc to get the object allocation traceback
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 = 1
Name = Skin, index = 1
Mapping capsBound attributes ................
Number of unique capsBound attributes = 3
Name = Skin_Top, index = 1
Name = Skin_Bottom, index = 2
Name = Skin_Tip, index = 3
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Skin, index = 1
Name = Rib_Root, index = 2
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 180
Number of elements = 194
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 32
Elemental Quad4 = 162
Getting FEA materials.......
Number of materials - 1
Material name - Madeupium
Done getting FEA materials
Getting FEA properties.......
Number of properties - 2
Property name - Rib_Root
Property name - Skin
Done getting FEA properties
Getting FEA constraints.......
Number of constraints - 1
Constraint name - edgeConstraint
No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement"
Done getting FEA constraints
Support tuple is NULL - No supports applied
Getting FEA loads.......
Number of loads - 1
Load name - pressureAero
No "groupName" specified for Load tuple pressureAero, going to use load name
Done getting FEA loads
Analysis tuple is NULL
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 16
Number of data points = 130
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 3.095062e+09, tgt = 3.095062e+09, diff = 1.283608e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 16
Number of data points = 130
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 3.012524e+09, tgt = 3.012524e+09, diff = 1.900412e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 16
Number of data points = 130
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 4.093856e+07, tgt = 4.093856e+07, diff = 3.967360e-04
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 81 (total = 81)
Extracting external pressure loads from data transfer....
TransferName = Skin_Bottom
Number of Elements = 81 (total = 162)
Extracting external pressure loads from data transfer....
TransferName = Skin_Tip
Number of Elements = 16 (total = 178)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R E S S E S for Subcase = 1
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R A I N S for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "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.
11576 grid points.
59941 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).
59941 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 1.713230 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_aeroelasticSimple_Iterative_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_SM.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_3|
+-----------------------------------------------------------------------+
| Far-field| BC_1|
+-----------------------------------------------------------------------+
| Symmetry plane| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
11576 grid points.
59941 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).
59941 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 257 TETRAHEDRON volume elements.
There has been a re-orientation of 4 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 63998.9.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 37.6885. Mean K: 0.668452. Standard deviation K: 2.43243.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 9.85102| 86.3467|
| CV Face Area Aspect Ratio| 1.13594| 89.958|
| CV Sub-Volume Ratio| 1| 9792.43|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 11576| 1/1.00| 10|
| 1| 2051| 1/5.64| 8.42481|
| 2| 412| 1/4.98| 7.40109|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 4.33426 m.
Wetted area = 39.4314 m^2.
Area projection in the x-plane = 16.6011 m^2, y-plane = 7.28077 m^2, z-plane = 3.36899 m^2.
Max. coordinate in the x-direction = 2.47071 m, y-direction = 4.33426 m, z-direction = 1.92982 m.
Min. coordinate in the x-direction = 0.00090365 m, y-direction = -2.85958e-18 m, z-direction = -6.26923 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| 5.8213e-01| 0.788412| 3.647455| 3.688071| 6.257518| -0.060572|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 6.0210e-01| 0.926404| 3.521903| 3.655705| 6.398752| -0.044565|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 6.0622e-01| 1.110372| 3.510517| 3.695432| 6.585852| -0.121795|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 1.11037| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Iterative_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Iterative_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
+-----------------------------------------------------------------------+
Warning: there are 14 non-physical points in the solution.
--------------------------- 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_aeroelasticSimple_Iterative_SM.csv
Number of variables = 16
Number of data points = 130
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 2.664353e+09, tgt = 2.664353e+09, diff = 3.508226e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 16
Number of data points = 130
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 2.268985e+09, tgt = 2.268987e+09, diff = 1.865381e+03
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 16
Number of data points = 130
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 2.905404e+07, tgt = 2.905404e+07, diff = 2.504364e-04
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 81 (total = 81)
Extracting external pressure loads from data transfer....
TransferName = Skin_Bottom
Number of Elements = 81 (total = 162)
Extracting external pressure loads from data transfer....
TransferName = Skin_Tip
Number of Elements = 16 (total = 178)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R E S S E S for Subcase = 1
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R A I N S for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "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.
11576 grid points.
59941 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).
59941 tetrahedra.
----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
There has been a re-orientation of 257 TETRAHEDRON volume elements.
There has been a re-orientation of 4 TRIANGLE surface elements.
Identify edges and vertices.
Setting the bound control volume structure.
Volume of the computational grid: 63998.9.
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 4.003593 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_aeroelasticSimple_Iterative_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_SM.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_3|
+-----------------------------------------------------------------------+
| Far-field| BC_1|
+-----------------------------------------------------------------------+
| Symmetry plane| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
11576 grid points.
59941 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).
59941 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 23867 TETRAHEDRON volume elements.
There has been a re-orientation of 1136 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 350877.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 270.747. Mean K: 1.97028. Standard deviation K: 10.3951.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 1.61284| 82.8911|
| CV Face Area Aspect Ratio| 1.41136| 514.223|
| CV Sub-Volume Ratio| 1| 82582|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 11576| 1/1.00| 10|
| 1| 2033| 1/5.69| 8.4001|
| 2| 407| 1/5| 7.37102|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 19.5836 m.
Wetted area = 1665.6 m^2.
Area projection in the x-plane = 994.91 m^2, y-plane = 193.929 m^2, z-plane = 12.5524 m^2.
Max. coordinate in the x-direction = 4.53487 m, y-direction = 19.5836 m, z-direction = 0.290264 m.
Min. coordinate in the x-direction = -0.00419033 m, y-direction = -2.85958e-18 m, z-direction = -218.672 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| 5.7986e-01| 3.470697| 6.426856| 6.507298| 8.939803| -0.061359|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 6.0107e-01| 3.787408| 6.398466| 6.437561| 9.261771| -0.047837|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 6.0445e-01| 3.842139| 6.387980| 6.456353| 9.242400| -0.048048|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 3.84214| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Iterative_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Iterative_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
+-----------------------------------------------------------------------+
Warning: there are 210 non-physical points in the solution.
Warning: 4 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_aeroelasticSimple_Iterative_SM.csv
Number of variables = 16
Number of data points = 130
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 1.370766e+09, tgt = 1.370766e+09, diff = 2.000770e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 16
Number of data points = 130
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 1.795778e+09, tgt = 1.795778e+09, diff = 3.770704e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 16
Number of data points = 130
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 1.181710e+07, tgt = 1.181710e+07, diff = 1.300369e-02
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 81 (total = 81)
Extracting external pressure loads from data transfer....
TransferName = Skin_Bottom
Number of Elements = 81 (total = 162)
Extracting external pressure loads from data transfer....
TransferName = Skin_Tip
Number of Elements = 16 (total = 178)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R E S S E S for Subcase = 1
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R A I N S for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "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.
11576 grid points.
59941 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).
59941 tetrahedra.
----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
There has been a re-orientation of 23867 TETRAHEDRON volume elements.
There has been a re-orientation of 1136 TRIANGLE surface elements.
Identify edges and vertices.
Setting the bound control volume structure.
Volume of the computational grid: 350877.
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 48.337895 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_aeroelasticSimple_Iterative_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_SM.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_3|
+-----------------------------------------------------------------------+
| Far-field| BC_1|
+-----------------------------------------------------------------------+
| Symmetry plane| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
11576 grid points.
59941 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).
59941 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 26102 TETRAHEDRON volume elements.
There has been a re-orientation of 1445 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 4.64445e+07.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 56.3493. Mean K: 1.26046. Standard deviation K: 3.98886.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 0.532342| 81.4902|
| CV Face Area Aspect Ratio| 1.58854| 4632.89|
| CV Sub-Volume Ratio| 1| 260169|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 11576| 1/1.00| 10|
| 1| 2056| 1/5.63| 8.43165|
| 2| 418| 1/4.92| 7.43684|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.81893 m.
Wetted area = 163.311 m^2.
Area projection in the x-plane = 51.4262 m^2, y-plane = 57.0487 m^2, z-plane = 7.8042 m^2.
Max. coordinate in the x-direction = 2.5401 m, y-direction = 7.81893 m, z-direction = 0.155398 m.
Min. coordinate in the x-direction = -0.00670967 m, y-direction = -2.85958e-18 m, z-direction = -52.7418 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| 4.4777e-01| 4.467594| 7.434429| 7.421672| 9.936700| 0.086723|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 4.6390e-01| 5.188820| 7.559183| 7.575496| 10.583015| 0.064144|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 4.7335e-01| 5.301792| 7.778016| 7.631154| 10.681597| 0.100685|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 5.30179| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Iterative_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Iterative_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
+-----------------------------------------------------------------------+
Warning: there are 401 non-physical points in the solution.
Warning: 26 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 = 25.206777
Cd = 250.352902
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 1m30.170s
user 1m23.170s
sys 0m6.870s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_SU2_and_Mystran.py passed (as expected)
=================================================
=================================================
+ echo 'aeroelasticSimple_Temperature_SU2_and_TACS.py test;'
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
aeroelasticSimple_Temperature_SU2_and_TACS.py test;
+ python -u aeroelasticSimple_Temperature_SU2_and_TACS.py -outLevel=0 -noPlotData
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR2 : Compile Date 07/25/23 @ 11:58AM
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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR4 : Compile Date 08/14/23 @ 01:20PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
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= 1334 2534 0
AFLR4 : Nodes, Trias,Quads= 1310 2486 0
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Trias,Quads= 1336 2538 0
AFLR4 : Nodes, Trias,Quads= 1319 2504 0
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Trias,Quads= 3810 7466 0
AFLR4 : Nodes, Trias,Quads= 2941 5728 0
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Trias,Quads= 1339 2544 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= 1319 2504 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= 9469 18934 946
OVERALL : CPU Time = 0.549 seconds
Body 1 (of 1)
Number of nodes = 9469
Number of elements = 18934
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 18934
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 9469
Total number of elements = 18934
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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR2 : Compile Date 07/25/23 @ 11:58AM
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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR4 : Compile Date 08/14/23 @ 01:20PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
Volume mesh:
Number of nodes = 60362
Number of elements = 347551
Number of triangles = 18934
Number of quadrilatarals = 0
Number of tetrahedrals = 328617
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......
/home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/io/config.py:142: ResourceWarning: unclosed file <_io.TextIOWrapper name='aeroelasticSimple_Temperature_SM.cfg' mode='r' encoding='UTF-8'>
konfig = read_config(filename)
ResourceWarning: Enable tracemalloc to get the object allocation traceback
/home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/io/config.py:933: ResourceWarning: unclosed file <_io.TextIOWrapper name='config_CFD.cfg_tmp' mode='r' encoding='UTF-8'>
for raw_line in open(temp_filename):
ResourceWarning: Enable tracemalloc to get the object allocation traceback
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) 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.
60362 grid points.
328617 volume elements.
3 surface markers.
12508 boundary elements in index 0 (Marker = BC_1).
5728 boundary elements in index 1 (Marker = BC_2).
698 boundary elements in index 2 (Marker = BC_3).
328617 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: 0.864202. Standard deviation K: 5.00891.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 54.7348| 87.2773|
| CV Face Area Aspect Ratio| 1.03373| 21.5651|
| CV Sub-Volume Ratio| 1| 7.81008|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 60362| 1/1.00| 10|
| 1| 10264| 1/5.88| 8.31015|
| 2| 1814| 1/5.66| 6.99531|
+-------------------------------------------+
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| 3.1090e+00| -1.356300| 0.924031| 0.585815| 4.112806| -0.971166|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.2396e+00| -1.752115| 0.771526| 0.411487| 3.703840| -0.590415|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.4361e+00| -1.758852| 0.590801| 0.239199| 3.698747| 1.356839|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.75885| < -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) ------------------------
/home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/run/interface.py:114: ResourceWarning: unclosed file <_io.BufferedReader name=4>
run_command(the_Command)
ResourceWarning: Enable tracemalloc to get the object allocation traceback
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 = 0
Total number of elements = 0
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 = 1.497419e+03, tgt = 1.497419e+03, diff = 9.105958e-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_Bottom' Normalized Integrated 'Temperature'
Rank 0: src = 1.453377e+03, tgt = 1.453377e+03, diff = 8.074436e-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 = 2.098171e+01, tgt = 2.098171e+01, diff = 2.060574e-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
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 0m32.075s
user 0m31.094s
sys 0m4.396s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Temperature_SU2_and_TACS.py passed (as expected)
=================================================
mystran: /home/jenkins/util/mystran/MYSTRAN/Binaries/mystran
flowCart: /home/jenkins/util/cart3d/cart3d_v1.5.9_X86_64_ICC--22.11.16/bin/X86_64_ICC//flowCart
=================================================
+ echo 'aeroelasticSimple_Iterative_Cart3D_and_Mystran.py test;'
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
aeroelasticSimple_Iterative_Cart3D_and_Mystran.py test;
+ python -u aeroelasticSimple_Iterative_Cart3D_and_Mystran.py -outLevel=0
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Skin, index = 1
Name = Rib_Root, index = 2
Body size = 4.649612
Tessellating body 1 with MaxEdge = 0.232481 Sag = 0.232481 Angle = 15.000000
Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 9 > autoInputs.out
-----------------------------------------------------
Suppressions used:
count bytes template
8 398574 *autoInputs
-----------------------------------------------------
Executing: ./aero.csh > aero.out
-----------------------------------------------------
Suppressions used:
count bytes template
1 40 *cubes
-----------------------------------------------------
-----------------------------------------------------
Suppressions used:
count bytes template
29 4116188 *mgPrep
-----------------------------------------------------
Cl = 0.11555834
Cd = 0.06178034
Mapping Csys attributes ................
Number of unique Csys attributes = 0
Getting FEA coordinate systems.......
Number of coordinate systems - 0
No coordinate systems found - defaulting to global
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = Rib_Root, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 1
Name = Skin, index = 1
Mapping capsBound attributes ................
Number of unique capsBound attributes = 3
Name = Skin_Top, index = 1
Name = Skin_Bottom, index = 2
Name = Skin_Tip, index = 3
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Skin, index = 1
Name = Rib_Root, index = 2
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 200
Number of elements = 234
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 72
Elemental Quad4 = 162
Getting FEA materials.......
Number of materials - 1
Material name - Madeupium
Done getting FEA materials
Getting FEA properties.......
Number of properties - 2
Property name - Rib_Root
Property name - Skin
Done getting FEA properties
Getting FEA constraints.......
Number of constraints - 1
Constraint name - edgeConstraint
No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement"
Done getting FEA constraints
Support tuple is NULL - No supports applied
Getting FEA loads.......
Number of loads - 1
Load name - pressureAero
No "groupName" specified for Load tuple pressureAero, going to use load name
Done getting FEA loads
Analysis tuple is NULL
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 2.207283e+04, tgt = 2.207283e+04, diff = 1.531398e-03
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 2.166467e+04, tgt = 2.166467e+04, diff = 2.374715e-03
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 3.226356e+02, tgt = 3.226356e+02, diff = 2.749681e-08
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 81 (total = 81)
Extracting external pressure loads from data transfer....
TransferName = Skin_Bottom
Number of Elements = 81 (total = 162)
Extracting external pressure loads from data transfer....
TransferName = Skin_Tip
Number of Elements = 36 (total = 198)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R E S S E S for Subcase = 1
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R A I N S for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 200
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 200
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 200
Loading displacements for Subcase = 1
Executing: ./aero.csh > aero.out
-----------------------------------------------------
Suppressions used:
count bytes template
1 40 *cubes
-----------------------------------------------------
-----------------------------------------------------
Suppressions used:
count bytes template
2 161128 *mgPrep
-----------------------------------------------------
Cl = 0.11583668
Cd = 0.063726594
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 2.204952e+04, tgt = 2.204952e+04, diff = 1.541534e-03
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 2.164530e+04, tgt = 2.164529e+04, diff = 1.937392e-03
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 3.220419e+02, tgt = 3.220419e+02, diff = 1.446659e-08
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 81 (total = 81)
Extracting external pressure loads from data transfer....
TransferName = Skin_Bottom
Number of Elements = 81 (total = 162)
Extracting external pressure loads from data transfer....
TransferName = Skin_Tip
Number of Elements = 36 (total = 198)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R E S S E S for Subcase = 1
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R A I N S for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 200
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 200
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 200
Loading displacements for Subcase = 1
Executing: ./aero.csh > aero.out
-----------------------------------------------------
Suppressions used:
count bytes template
1 40 *cubes
-----------------------------------------------------
-----------------------------------------------------
Suppressions used:
count bytes template
29 4062300 *mgPrep
-----------------------------------------------------
Cl = 0.11639576
Cd = 0.063776668
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 2.204945e+04, tgt = 2.204944e+04, diff = 1.541197e-03
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 2.164654e+04, tgt = 2.164653e+04, diff = 2.006886e-03
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 3.220000e+02, tgt = 3.220000e+02, diff = 2.027377e-09
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 81 (total = 81)
Extracting external pressure loads from data transfer....
TransferName = Skin_Bottom
Number of Elements = 81 (total = 162)
Extracting external pressure loads from data transfer....
TransferName = Skin_Tip
Number of Elements = 36 (total = 198)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R E S S E S for Subcase = 1
Reading Mystran FO6 file!
Number of Elements = 162
Loading E L E M E N T S T R A I N S for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 200
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 200
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 200
Loading displacements for Subcase = 1
Executing: ./aero.csh > aero.out
-----------------------------------------------------
Suppressions used:
count bytes template
1 40 *cubes
-----------------------------------------------------
-----------------------------------------------------
Suppressions used:
count bytes template
29 4061740 *mgPrep
-----------------------------------------------------
Cl = 0.11659925
Cd = 0.063844128
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 2m51.814s
user 4m8.836s
sys 0m52.648s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_Cart3D_and_Mystran.py passed (as expected)
=================================================
*************************************************
*************************************************
=================================================
Did not run examples for:
Astros
=================================================
All tests pass!
[GNU C Compiler (gcc)] Parsing console log (workspace: '/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[Clang] Skipping post processing
[Clang] No filter has been set, publishing all 0 issues
[Clang] Repository miner is not configured, skipping repository mining
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[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: '/jenkins/workspace/ESP_MemcheckCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[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] Obtaining reference build from same job (7.6,CAPS/AEROELASTIC,LINUX64,reynolds)
[Static Analysis] Using reference build 'ESP_MemcheckCaps/CASREV=7.6,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=LINUX64,buildnode=reynolds #1308' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1
[Static Analysis] -> All quality gates have been passed
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_MemcheckCaps/CASREV=7.6,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=LINUX64,buildnode=reynolds #1309'.
[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
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