Skipping 4,332 KB..
Full LogWetted area = 8795.17 m^2.
Area projection in the x-plane = 681.447 m^2, y-plane = 449.382 m^2, z-plane = 4224.13 m^2.
Max. coordinate in the x-direction = 123.552 m, y-direction = 97.6729 m, z-direction = 4.71806 m.
Min. coordinate in the x-direction = 49.9621 m, y-direction = -97.6729 m, z-direction = -8.47903 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 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| 221265| 1| m^2/s^2| 221265|
| Velocity-X| 170.123| 1| m/s| 170.123|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 2.9695| 1| m/s| 2.9695|
| Velocity Magnitude| 170.149| 1| m/s| 170.149|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.5|
+------------------------------------------------------------------------------+
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| 4.3227e+01| 0.368330| 2.648238| 2.121327| 5.851176| -0.410308|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 4.1628e+01| 2.535891| 5.048674| 4.743726| 8.017676| -0.061400|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.9752e+01| 4.002957| 6.556330| 6.228550| 9.495336| 1.359163|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.9452e+01| 5.533471| 8.048225| 7.830955| 11.027353| -4.557569|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.8957e+01| 6.253620| 8.891330| 8.699682| 11.768084| 2.534539|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 3.9205e+01| 6.493163| 8.882225| 8.893144| 11.883202| -60.520242|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 3.8747e+01| 9.200667| 11.738524| 11.988387| 14.912223| -44.365071|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 3.8766e+01| 8.651940| 11.071123| 11.325719| 14.421711| -44.906622|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 3.8782e+01| 7.975125| 10.276237| 10.558965| 13.778098| -50.173087|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 3.8602e+01| 7.947052| 10.255228| 10.669433| 13.780858| -63.785246|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 7.94705| < -8| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_inviscidWing.dat |
Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
|CSV file |surface_flow_inviscidWing.csv |
Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
|Paraview |flow_inviscidWing.vtu |
Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
|Paraview surface |surface_flow_inviscidWing.vtu |
Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
+-----------------------------------------------------------------------+
Warning: there are 224 non-physical points in the solution.
Warning: 72 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) ------------------------
==> Total Forces and Moments
--> Cl = -122.955647 Cd = 1.92765
--> Cmx = 1.112673 Cmy = 19.458061 Cmz = 0.9617
--> Cx = 4.073229 Cy = 2.512085 Cz = -122.903279
real 15m12.337s
user 14m42.734s
sys 0m11.146s
+ status=0
+ set +x
=================================================
data/session08/2_su2_InviscidWing.py passed (as expected)
=================================================
=================================================
1_astros_ModalCantilever.py test;
+ python 1_astros_ModalCantilever.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "../ESP/transport.csm"...
==> Running mASTROS pre-analysis...
MESSAGE:: Building wingOml
MESSAGE:: Building wingWaffle
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 2
Name = wingSpar1, index = 1
Name = wingSpar2, index = 2
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 425
Number of elements = 482
Number of triangle elements = 0
Number of quadrilateral elements = 482
----------------------------
Total number of nodes = 425
Total number of elements = 482
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 4
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Name = leftPointLoad, index = 3
Name = ritePointLoad, index = 4
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 425
Number of elements = 482
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 482
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Load tuple is NULL - No loads applied
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Getting FEA analyses.......
Number of analyses - 1
Analysis name - EigenAnalysis
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!!
Writing analysis cards
Writing constraint cards--all constraints for each subcase
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
==> Running mASTROS post-analysis...
Reading Astros OUT file - extracting Eigen-Values!
Number of Eigen-Values = 10
Loading Eigen-Value = 1
Loading Eigen-Value = 2
Loading Eigen-Value = 3
Loading Eigen-Value = 4
Loading Eigen-Value = 5
Loading Eigen-Value = 6
Loading Eigen-Value = 7
Loading Eigen-Value = 8
Loading Eigen-Value = 9
Loading Eigen-Value = 10
--> Eigen-frequencies:
1 : 0.00145606
2 : 0.0014575
3 : 0.00332859
4 : 0.00333096
5 : 0.00445176
6 : 0.00445507
7 : 0.00894917
8 : 0.0089521
9 : 0.0110353
10: 0.0110413
real 0m48.546s
user 1m21.316s
sys 2m40.107s
+ status=0
+ set +x
=================================================
data/session09/1_astros_ModalCantilever.py passed (as expected)
=================================================
=================================================
2_astros_ModalSupport.py test;
+ python 2_astros_ModalSupport.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "../ESP/transport.csm"...
==> Running mASTROS pre-analysis...
MESSAGE:: Building wingOml
MESSAGE:: Building wingWaffle
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Name = ribSupport, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 2
Name = wingSpar1, index = 1
Name = wingSpar2, index = 2
Getting surface mesh for body 1 (of 2)
Getting surface mesh for body 2 (of 2)
Body 1 (of 2)
Number of nodes = 832
Number of elements = 963
Number of triangle elements = 0
Number of quadrilateral elements = 963
Body 2 (of 2)
Number of nodes = 1
Number of elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 833
Total number of elements = 963
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = ribRootPoint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = leftPointLoad, index = 1
Name = ritePointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 1
Name = ribRoot, index = 1
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Name = ribSupport, index = 6
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 832
Number of elements = 963
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 963
Setting FEA Data
Mesh for body = 1
Number of nodal coordinates = 1
Number of elements = 1
Elemental Nodes = 1
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 0
Combining multiple FEA meshes!
Combined Number of nodal coordinates = 833
Combined Number of elements = 964
Combined Elemental Nodes = 1
Combined Elemental Rods = 0
Combined Elemental Tria3 = 0
Combined Elemental Quad4 = 963
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 6
Property name - leftWingSkin
Property name - ribSupport
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - ribRootPoint
No "constraintType" specified for Constraint tuple ribRootPoint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple ribRootPoint, going to use constraint name
Done getting FEA constraints
Getting FEA supports.......
Number of supports - 1
Support name - ribRootPoint
No "groupName" specified for Support tuple ribRootPoint, going to use support name
Done getting FEA supports
Getting FEA connections.......
Number of connection tuples - 1
Connection name - ribRoot
No "groupName" specified for Connection tuple ribRoot!
Looking for automatic connections from the use of capsConnectLink for ribRoot
9 automatic connections were made for capsConnect ribRoot (node id 833)
Done getting FEA connections
Load tuple is NULL - No loads applied
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Getting FEA analyses.......
Number of analyses - 1
Analysis name - EigenAnalysis
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing connection cards - appending mesh file
Writing Astros instruction file....
Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!!
Writing analysis cards
Writing constraint cards--all constraints for each subcase
Writing support cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
==> Running mASTROS post-analysis...
Reading Astros OUT file - extracting Eigen-Values!
Number of Eigen-Values = 10
Loading Eigen-Value = 1
Loading Eigen-Value = 2
Loading Eigen-Value = 3
Loading Eigen-Value = 4
Loading Eigen-Value = 5
Loading Eigen-Value = 6
Loading Eigen-Value = 7
Loading Eigen-Value = 8
Loading Eigen-Value = 9
Loading Eigen-Value = 10
--> Eigen-frequencies:
1 : 0.00141994
2 : 0.0017446
3 : 0.00322974
4 : 0.00324319
5 : 0.00432862
6 : 0.00512378
7 : 0.0087335
8 : 0.0100598
9 : 0.010673
10: 0.0107176
real 1m36.522s
user 2m37.555s
sys 9m37.089s
+ status=0
+ set +x
=================================================
data/session09/2_astros_ModalSupport.py passed (as expected)
=================================================
=================================================
3_astros_StaticCantilever.py test;
+ python 3_astros_StaticCantilever.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "../ESP/transport.csm"...
==> Running mASTROS pre-analysis...
MESSAGE:: Building wingOml
MESSAGE:: Building wingWaffle
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 2
Name = wingSpar1, index = 1
Name = wingSpar2, index = 2
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 425
Number of elements = 482
Number of triangle elements = 0
Number of quadrilateral elements = 482
----------------------------
Total number of nodes = 425
Total number of elements = 482
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 4
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Name = leftPointLoad, index = 3
Name = ritePointLoad, index = 4
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 425
Number of elements = 482
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 482
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 2
Load name - leftPointLoad
No "groupName" specified for Load tuple leftPointLoad, going to use load name
Load name - ritePointLoad
No "groupName" specified for Load tuple ritePointLoad, going to use load name
Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
==> Running mASTROS post-analysis...
--> Maximum displacements:
--> Tmax 238433.3403112283
--> T1max 16861.9
--> T2max 16414.9
--> T3max 237286.0
real 0m43.107s
user 1m16.996s
sys 5m17.082s
+ status=0
+ set +x
=================================================
data/session09/3_astros_StaticCantilever.py passed (as expected)
=================================================
=================================================
4_astros_Composite.py test;
+ python 4_astros_Composite.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "../ESP/transport.csm"...
MESSAGE:: Building wingOml
MESSAGE:: Building wingWaffle
==> Running mASTROS pre-analysis...
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 2
Name = wingSpar1, index = 1
Name = wingSpar2, index = 2
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 425
Number of elements = 482
Number of triangle elements = 0
Number of quadrilateral elements = 482
----------------------------
Total number of nodes = 425
Total number of elements = 482
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 4
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Name = leftPointLoad, index = 3
Name = ritePointLoad, index = 4
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 425
Number of elements = 482
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 482
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Aluminum
No "materialType" specified for Material tuple Aluminum, defaulting to "Isotropic"
Material name - Graphite_epoxy
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 2
Load name - leftPointLoad
No "groupName" specified for Load tuple leftPointLoad, going to use load name
Load name - ritePointLoad
No "groupName" specified for Load tuple ritePointLoad, going to use load name
Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
==> Running mASTROS post-analysis...
--> Maximum displacements:
--> Tmax 52594.60117638786
--> T1max 4359.68
--> T2max 3216.5
--> T3max 52322.2
real 0m42.565s
user 1m15.989s
sys 4m36.398s
+ status=0
+ set +x
=================================================
data/session09/4_astros_Composite.py passed (as expected)
=================================================
[1723355010.507399] [reynolds:276906:0] ucp_context.c:1774 UCX WARN UCP version is incompatible, required: 1.16, actual: 1.12 (release 1)
=================================================
6_tacs_StaticCantilever.py test;
+ python 6_tacs_StaticCantilever.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
[1723355013.567861] [reynolds:276974:0] ucp_context.c:1774 UCX WARN UCP version is incompatible, required: 1.16, actual: 1.12 (release 1)
==> Loading geometry from file "../ESP/transport.csm"...
==> Running TACS pre-analysis...
MESSAGE:: Building wingOml
MESSAGE:: Building wingWaffle
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 2
Name = wingSpar1, index = 1
Name = wingSpar2, index = 2
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 425
Number of elements = 482
Number of triangle elements = 0
Number of quadrilateral elements = 482
----------------------------
Total number of nodes = 425
Total number of elements = 482
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 4
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Name = leftPointLoad, index = 3
Name = ritePointLoad, index = 4
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 425
Number of elements = 482
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 482
Getting FEA materials.......
Number of materials - 1
Material name - aluminum
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 2
Load name - leftWingSkin
No "groupName" specified for Load tuple leftWingSkin, going to use load name
Load name - riteWingSkin
No "groupName" specified for Load tuple riteWingSkin, 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
Writing Nastran grid and connectivity file (in large 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
Writing coordinate system cards
[0] Creating TACSAssembler with numOwnedNodes = 425 numElements = 482
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 2.84, nnz(ILU) = 11729
==> Running TACS...
==> Running TACS post-analysis...
Tacs Analysis Outputs...
functional mass = 511406.7093890694
functional ks_vmfailure = 0.019135051727262598
real 0m43.808s
user 1m19.247s
sys 5m57.201s
+ status=0
+ set +x
=================================================
data/session09/6_tacs_StaticCantilever.py passed (as expected)
=================================================
=================================================
7_tacs_sizing.py test;
+ python 7_tacs_sizing.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
[1723355057.308421] [reynolds:278833:0] ucp_context.c:1774 UCX WARN UCP version is incompatible, required: 1.16, actual: 1.12 (release 1)
==> Loading geometry from file "../ESP/transport.csm"...
==> Starting optimization...
MESSAGE:: Building wingOml
MESSAGE:: Building wingWaffle
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 2
Name = wingSpar1, index = 1
Name = wingSpar2, index = 2
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 3852
Number of elements = 4061
Number of triangle elements = 0
Number of quadrilateral elements = 4061
----------------------------
Total number of nodes = 3852
Total number of elements = 4061
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 4
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Name = leftPointLoad, index = 3
Name = ritePointLoad, index = 4
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 3852
Number of elements = 4061
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 4061
Getting FEA materials.......
Number of materials - 1
Material name - aluminum
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 2
Load name - leftWingSkin
No "groupName" specified for Load tuple leftWingSkin, going to use load name
Load name - riteWingSkin
No "groupName" specified for Load tuple riteWingSkin, going to use load name
Done getting FEA loads
Getting FEA design variables.......
Number of design variables - 3
Design_Variable name - ribThk
Design_Variable name - skinThk
Design_Variable name - sparThk
Design_Variable_Relation name - relLeftSkin
Design_Variable_Relation name - relRib
Design_Variable_Relation name - relRiteSkin
Design_Variable_Relation name - relSpar
Number of design variable relations - 4
Done getting FEA design variables
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
Writing Nastran grid and connectivity file (in large 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
Writing coordinate system cards
Writing design variable cards
Writing design variable relation cards
[0] Creating TACSAssembler with numOwnedNodes = 3852 numElements = 4061
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/data/session09/7_tacs_sizing.py:144: DeprecationWarning: Conversion of an array with ndim > 0 to a scalar is deprecated, and will error in future. Ensure you extract a single element from your array before performing this operation. (Deprecated NumPy 1.25.)
xarray[ithick] = float(inputs[thick_dv])
--> ribThk [0.05]
--> skinThk [0.003]
--> sparThk [0.1]
--> mass [351348.85843759]
--> ks_vmfailure [0.18465374]
--> mass [351348.85843759]
--> ks_vmfailure [0.18465374]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00701607]]
--> ks_vmfailure skinThk [[-0.7773577]]
--> ks_vmfailure sparThk [[-0.00419852]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.001]
--> skinThk [0.00739074]
--> sparThk [0.001]
--> mass [164778.06693791]
--> ks_vmfailure [0.18458271]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.27193779]]
--> ks_vmfailure skinThk [[-0.30939955]]
--> ks_vmfailure sparThk [[-0.20978604]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.001]
--> skinThk [0.001]
--> sparThk [0.02273644]
--> mass [129232.41451658]
--> ks_vmfailure [0.20239501]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.001]
--> skinThk [0.00647627]
--> sparThk [0.00411034]
--> mass [159691.72857107]
--> ks_vmfailure [0.18468723]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.28428468]]
--> ks_vmfailure skinThk [[-0.36623706]]
--> ks_vmfailure sparThk [[-0.04561164]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.01797054]
--> skinThk [0.001]
--> sparThk [0.0012247]
--> mass [135761.31369163]
--> ks_vmfailure [0.20097432]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00336292]
--> skinThk [0.00571377]
--> sparThk [0.00370855]
--> mass [156359.73960161]
--> ks_vmfailure [0.18476613]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.04724024]]
--> ks_vmfailure skinThk [[-0.42968566]]
--> ks_vmfailure sparThk [[-0.05558717]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00375419]
--> skinThk [0.0118629]
--> sparThk [0.00560564]
--> mass [221348.4685629]
--> ks_vmfailure [0.18335024]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00340205]
--> skinThk [0.00632869]
--> sparThk [0.00389826]
--> mass [162858.61249774]
--> ks_vmfailure [0.18451389]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.0033671]
--> skinThk [0.00577947]
--> sparThk [0.00372882]
--> mass [157054.09505636]
--> ks_vmfailure [0.18473688]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.04660765]]
--> ks_vmfailure skinThk [[-0.4208561]]
--> ks_vmfailure sparThk [[-0.05458697]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.001]
--> skinThk [0.0114244]
--> sparThk [0.01236645]
--> mass [220187.17380918]
--> ks_vmfailure [0.18349008]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.2237631]]
--> ks_vmfailure skinThk [[-0.11542907]]
--> ks_vmfailure sparThk [[-0.00924893]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00726772]
--> skinThk [0.01192034]
--> sparThk [0.01564751]
--> mass [242329.88496499]
--> ks_vmfailure [0.18318718]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00374643]
--> skinThk [0.01164171]
--> sparThk [0.01380417]
--> mass [229889.80121865]
--> ks_vmfailure [0.18327675]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.0024241]
--> skinThk [0.01153708]
--> sparThk [0.01311195]
--> mass [225218.27320809]
--> ks_vmfailure [0.18333401]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.04342338]]
--> ks_vmfailure skinThk [[-0.10932276]]
--> ks_vmfailure sparThk [[-0.00862543]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00273423]
--> skinThk [0.02300858]
--> sparThk [0.0208162]
--> mass [351071.64820344]
--> ks_vmfailure [0.18265072]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00246133]
--> skinThk [0.01291395]
--> sparThk [0.01403666]
--> mass [240323.86265565]
--> ks_vmfailure [0.18319035]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.04030186]]
--> ks_vmfailure skinThk [[-0.08766022]]
--> ks_vmfailure sparThk [[-0.00725048]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00615236]
--> skinThk [0.02577931]
--> sparThk [0.00214914]
--> mass [361343.30237147]
--> ks_vmfailure [0.18263733]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00640621]]
--> ks_vmfailure skinThk [[-0.02501964]]
--> ks_vmfailure sparThk [[-0.04131364]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00713229]
--> skinThk [0.02677305]
--> sparThk [0.01682207]
--> mass [392609.48008805]
--> ks_vmfailure [0.18251681]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00663017]
--> skinThk [0.02626385]
--> sparThk [0.00930362]
--> mass [376588.6096398]
--> ks_vmfailure [0.18255199]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00641281]
--> skinThk [0.02604342]
--> sparThk [0.00604887]
--> mass [369653.14723749]
--> ks_vmfailure [0.18257185]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00605012]]
--> ks_vmfailure skinThk [[-0.02434576]]
--> ks_vmfailure sparThk [[-0.00555071]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00973722]
--> skinThk [0.04835412]
--> sparThk [0.00759187]
--> mass [602336.92628688]
--> ks_vmfailure [0.18225672]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.00752074]
--> skinThk [0.03347893]
--> sparThk [0.00656311]
--> mass [447199.86601843]
--> ks_vmfailure [0.18242234]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00423674]]
--> ks_vmfailure skinThk [[-0.01486487]]
--> ks_vmfailure sparThk [[-0.00451752]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.01240421]
--> skinThk [0.05849074]
--> sparThk [0.01317188]
--> mass [716839.28219105]
--> ks_vmfailure [0.18217977]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00154607]]
--> ks_vmfailure skinThk [[-0.00498159]]
--> ks_vmfailure sparThk [[-0.00115577]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.01929413]
--> skinThk [0.09078534]
--> sparThk [0.02029655]
--> mass [1064338.2244386]
--> ks_vmfailure [0.18206339]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00064649]]
--> ks_vmfailure skinThk [[-0.00208486]]
--> ks_vmfailure sparThk [[-0.00048512]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.02545588]
--> skinThk [0.11766684]
--> sparThk [0.0272289]
--> mass [1355782.71803893]
--> ks_vmfailure [0.18201458]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.0003768]]
--> ks_vmfailure skinThk [[-0.00124124]]
--> ks_vmfailure sparThk [[-0.00027327]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.02816251]
--> skinThk [0.1278486]
--> sparThk [0.0306149]
--> mass [1467935.35100916]
--> ks_vmfailure [0.1820012]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00031099]]
--> ks_vmfailure skinThk [[-0.00105064]]
--> ks_vmfailure sparThk [[-0.00021913]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.02874643]
--> skinThk [0.12860074]
--> sparThk [0.03166047]
--> mass [1478053.27821022]
--> ks_vmfailure [0.18200001]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00030043]]
--> ks_vmfailure skinThk [[-0.00103744]]
--> ks_vmfailure sparThk [[-0.00020726]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.02995585]
--> skinThk [0.12773278]
--> sparThk [0.03432141]
--> mass [1475323.27729737]
--> ks_vmfailure [0.18200005]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00028252]]
--> ks_vmfailure skinThk [[-0.00104812]]
--> ks_vmfailure sparThk [[-0.00018401]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03300208]
--> skinThk [0.1258291]
--> sparThk [0.04074924]
--> mass [1470920.55147938]
--> ks_vmfailure [0.18200021]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00024502]]
--> ks_vmfailure skinThk [[-0.00107038]]
--> ks_vmfailure sparThk [[-0.00014848]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03417054]
--> skinThk [0.12543857]
--> sparThk [0.04303491]
--> mass [1472403.17570301]
--> ks_vmfailure [0.18200002]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00023279]]
--> ks_vmfailure skinThk [[-0.00107335]]
--> ks_vmfailure sparThk [[-0.00014019]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.0346654]
--> skinThk [0.12523006]
--> sparThk [0.04393554]
--> mass [1472509.96840742]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00022797]]
--> ks_vmfailure skinThk [[-0.00107536]]
--> ks_vmfailure sparThk [[-0.00013746]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03477346]
--> skinThk [0.12519386]
--> sparThk [0.04405885]
--> mass [1472530.51739648]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00022693]]
--> ks_vmfailure skinThk [[-0.00107573]]
--> ks_vmfailure sparThk [[-0.00013712]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03499382]
--> skinThk [0.12513458]
--> sparThk [0.0441599]
--> mass [1472520.46425353]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00022479]]
--> ks_vmfailure skinThk [[-0.00107642]]
--> ks_vmfailure sparThk [[-0.00013689]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.035286]
--> skinThk [0.12508834]
--> sparThk [0.04404567]
--> mass [1472505.61302732]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00022196]]
--> ks_vmfailure skinThk [[-0.00107708]]
--> ks_vmfailure sparThk [[-0.00013735]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.0355475]
--> skinThk [0.12509498]
--> sparThk [0.0435743]
--> mass [1472488.97921078]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.0002194]]
--> ks_vmfailure skinThk [[-0.0010773]]
--> ks_vmfailure sparThk [[-0.00013892]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03557543]
--> skinThk [0.12515335]
--> sparThk [0.04308254]
--> mass [1472485.56114736]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00021902]]
--> ks_vmfailure skinThk [[-0.00107687]]
--> ks_vmfailure sparThk [[-0.00014054]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03549811]
--> skinThk [0.12518987]
--> sparThk [0.04292621]
--> mass [1472487.80119021]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.0002197]]
--> ks_vmfailure skinThk [[-0.00107651]]
--> ks_vmfailure sparThk [[-0.00014103]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03546495]
--> skinThk [0.12519741]
--> sparThk [0.04292079]
--> mass [1472488.3611772]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00022001]]
--> ks_vmfailure skinThk [[-0.00107642]]
--> ks_vmfailure sparThk [[-0.00014104]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03546229]
--> skinThk [0.12519748]
--> sparThk [0.04292444]
--> mass [1472488.41090652]
--> ks_vmfailure [0.182]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03546377]
--> skinThk [0.12519744]
--> sparThk [0.04292241]
--> mass [1472488.38326913]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.65486045]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00022002]]
--> ks_vmfailure skinThk [[-0.00107641]]
--> ks_vmfailure sparThk [[-0.00014103]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03546228]
--> skinThk [0.12519745]
--> sparThk [0.0429247]
--> mass [1472488.41133957]
--> ks_vmfailure [0.182]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03546335]
--> skinThk [0.12519744]
--> sparThk [0.04292305]
--> mass [1472488.3910861]
--> ks_vmfailure [0.182]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03546373]
--> skinThk [0.12519744]
--> sparThk [0.04292248]
--> mass [1472488.38405081]
--> ks_vmfailure [0.182]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.80, nnz(ILU) = 208272
--> ribThk [0.03546376]
--> skinThk [0.12519744]
--> sparThk [0.04292242]
--> mass [1472488.38334728]
--> ks_vmfailure [0.182]
Optimization terminated successfully (Exit mode 0)
Current function value: 4.207109666706528
Iterations: 28
Function evaluations: 43
Gradient evaluations: 28
Optimization Complete
-----------------------------------
==> Optimized value:
--> ribThk [0.03546376]
--> skinThk [0.12519744]
--> sparThk [0.04292242]
real 3m37.499s
user 4m52.533s
sys 5m33.784s
+ status=0
+ set +x
=================================================
data/session09/7_tacs_sizing.py passed (as expected)
=================================================
=================================================
2_aeroelastic_Iterative_SU2_Astros.py test;
+ python 2_aeroelastic_Iterative_SU2_Astros.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
MESSAGE:: Building wingOml
MESSAGE:: Building wingWaffle
==> Running SU2 pre-analysis...
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Wing, index = 1
Name = Farfield, index = 2
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = leftWing, index = 1
Name = riteWing, index = 2
Name = Farfield, index = 3
Getting mesh sizing parameters
Mesh sizing name - Farfield
Mesh sizing name - leftWing
Mesh sizing name - riteWing
Done getting mesh sizing parameters
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.18.1
AFLR2 : Version Date 06/11/24 @ 05:52PM
AFLR2 : Compile OS Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR2 : Compile Date 06/11/24 @ 06:33PM
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 11.5.15
AFLR4 : Version Date 07/19/24 @ 07:04PM
AFLR4 : Compile OS Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR4 : Compile Date 07/19/24 @ 07:42PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.27
EGADS : OpenCASCADE Version 7.8.1
EGADS : ---------------------------------------
EGADS : EGADS CAD Geometry Setup
EGADS : Model has 2 Active Bodies
EGADS : Body 0 is a SolidBody
EGADS : Body 0 has 1 Shells
EGADS : Body 0 has 10 Faces
EGADS : Body 0 has 18 Edges
EGADS : Body 0 has 10 Loops
EGADS : Body 0 has 10 Nodes
EGADS : Body 1 is a SolidBody
EGADS : Body 1 has 1 Shells
EGADS : Body 1 has 6 Faces
EGADS : Body 1 has 12 Edges
EGADS : Body 1 has 6 Loops
EGADS : Body 1 has 8 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 0.5 1 2 3 6
EGADS : 2 Yes 0 0 1 0.5 1 1 4 5
EGADS : 3 Yes 0 0 1 0.5 1 1 4 8
EGADS : 4 Yes 0 0 1 0.5 1 2 3 5
EGADS : 5 Yes 0 0 1 0.5 1 2 4
EGADS : 6 Yes 0 0 1 0.5 1 1 7 8
EGADS : 7 Yes 0 0 1 0.5 1 6 9 10
EGADS : 8 Yes 0 0 1 0.5 1 3 6 9
EGADS : 9 Yes 0 0 1 0.5 1 7 8 10
EGADS : 10 Yes 0 0 1 0.5 1 7 9
EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16
EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16
EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16
EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16
EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14
EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14
EGADS : Face Edges Information
EGADS : Face Edges
EGADS : 1 -1 2 3 -4
EGADS : 2 -5 4 6 -7
EGADS : 3 -3 8 1 -9
EGADS : 4 -6 9 5 -10
EGADS : 5 7 10
EGADS : 6 11 13 -12 -2
EGADS : 7 14 16 -15 -13
EGADS : 8 12 17 -11 -8
EGADS : 9 15 18 -14 -17
EGADS : 10 -16 -18
EGADS : 11 19 20 -21 -22
EGADS : 12 -23 26 25 -24
EGADS : 13 27 23 -28 -19
EGADS : 14 -29 21 30 -25
EGADS : 15 22 29 -26 -27
EGADS : 16 -20 28 24 -30
EGADS : Face Loops Information
EGADS : Face Loops
EGADS : 1 1
EGADS : 2 2
EGADS : 3 3
EGADS : 4 4
EGADS : 5 5
EGADS : 6 6
EGADS : 7 7
EGADS : 8 8
EGADS : 9 9
EGADS : 10 10
EGADS : 11 11
EGADS : 12 12
EGADS : 13 13
EGADS : 14 14
EGADS : 15 15
EGADS : 16 16
EGADS : Loop Edges Information
EGADS : Loop Active Edges
EGADS : 1 Yes -1 2 3 -4
EGADS : 2 Yes -5 4 6 -7
EGADS : 3 Yes -3 8 1 -9
EGADS : 4 Yes -6 9 5 -10
EGADS : 5 Yes 7 10
EGADS : 6 Yes 11 13 -12 -2
EGADS : 7 Yes 14 16 -15 -13
EGADS : 8 Yes 12 17 -11 -8
EGADS : 9 Yes 15 18 -14 -17
EGADS : 10 Yes -16 -18
EGADS : 11 Yes 19 20 -21 -22
EGADS : 12 Yes -23 26 25 -24
EGADS : 13 Yes 27 23 -28 -19
EGADS : 14 Yes -29 21 30 -25
EGADS : 15 Yes 22 29 -26 -27
EGADS : 16 Yes -20 28 24 -30
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 1 2 1 1 3
EGADS : 2 0 Yes 1 3 1 1 6
EGADS : 3 0 Yes 3 4 1 1 3
EGADS : 4 0 Yes 2 4 1 1 2
EGADS : 5 0 Yes 2 5 1 2 4
EGADS : 6 0 Yes 4 6 1 2 4
EGADS : 7 0 Yes 5 6 1 2 5
EGADS : 8 0 Yes 3 1 1 3 8
EGADS : 9 0 Yes 4 2 1 3 4
EGADS : 10 0 Yes 6 5 1 4 5
EGADS : 11 0 Yes 1 7 1 6 8
EGADS : 12 0 Yes 3 8 1 6 8
EGADS : 13 0 Yes 7 8 1 6 7
EGADS : 14 0 Yes 7 9 1 7 9
EGADS : 15 0 Yes 8 10 1 7 9
EGADS : 16 0 Yes 9 10 1 7 10
EGADS : 17 0 Yes 8 7 1 8 9
EGADS : 18 0 Yes 10 9 1 9 10
EGADS : 19 1 Yes 12 11 NA 11 13
EGADS : 20 1 Yes 11 13 NA 11 16
EGADS : 21 1 Yes 14 13 NA 11 14
EGADS : 22 1 Yes 12 14 NA 11 15
EGADS : 23 1 Yes 16 15 NA 12 13
EGADS : 24 1 Yes 15 17 NA 12 16
EGADS : 25 1 Yes 18 17 NA 12 14
EGADS : 26 1 Yes 16 18 NA 12 15
EGADS : 27 1 Yes 12 16 NA 13 15
EGADS : 28 1 Yes 11 15 NA 13 16
EGADS : 29 1 Yes 14 18 NA 14 15
EGADS : 30 1 Yes 13 17 NA 14 16
EGADS : Node Information
EGADS : Node Active Coordinates
EGADS : 1 Yes 97.2007855 0 0
EGADS : 2 Yes 97.9335611 0 0
EGADS : 3 Yes 50 0 0
EGADS : 4 Yes 75.3047874 0 0
EGADS : 5 Yes 123.552357 0 4.7180639
EGADS : 6 Yes 118.391317 0 3.99272703
EGADS : 7 Yes 97.9335611 36.1389817 0
EGADS : 8 Yes 75.3047874 36.1389817 0
EGADS : 9 Yes 123.552357 97.6729236 4.7180639
EGADS : 10 Yes 118.391317 97.6729236 3.99272703
EGADS : 11 Yes 0 0 1951.57774
EGADS : 12 Yes 0 0 0
EGADS : 13 Yes 0 1953.45847 1951.57774
EGADS : 14 Yes 0 1953.45847 0
EGADS : 15 Yes 2040.21562 0 1951.57774
EGADS : 16 Yes 2040.21562 0 0
EGADS : 17 Yes 2040.21562 1953.45847 1951.57774
EGADS : 18 Yes 2040.21562 1953.45847 0
EGADS : Face and Edge Match Information
EGADS : No Face Matches Found
AFLR4 : Surface Mesh Spacing Setup
AFLR4 : Max Bounding Box Length = 3906.92
AFLR4 : Min Bounding Box Length = 3906.92
AFLR4 : Max Ref Bounding Box Length = 195.346
AFLR4 : Min Ref Bounding Box Length = 13.1976
AFLR4 : Reference Length = 21.7051
AFLR4 : BL Thickness = 0
AFLR4 : FarField Spacing = 11135.8
AFLR4 : Abs Min Surf Spacing = 0.0542627
AFLR4 : Min Surf Spacing = 0.108525
AFLR4 : Max Surf Spacing = 2.17051
AFLR4 : Global Scale Factor = 16
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 : 10 CAD geometry 0 STD w/BL
AFLR4 : 11 CAD geometry 0 FARFIELD
AFLR4 : 12 CAD geometry 0 FARFIELD
AFLR4 : 13 CAD geometry 0 FARFIELD
AFLR4 : 14 CAD geometry 0 FARFIELD
AFLR4 : 15 CAD geometry 0 FARFIELD
AFLR4 : 16 CAD geometry 0 FARFIELD
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 : Define CAD surface definition 10
AFLR4 : Define CAD surface definition 11
AFLR4 : Define CAD surface definition 12
AFLR4 : Define CAD surface definition 13
AFLR4 : Define CAD surface definition 14
AFLR4 : Define CAD surface definition 15
AFLR4 : Define CAD surface definition 16
AFLR4 : Surface Grid Generation
AFLR4 : Generate optimal mesh on surface definition 1
AFLR2 : Nodes, Trias,Quads= 242 426 0
AFLR4 : Nodes, Trias,Quads= 203 348 0
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Trias,Quads= 301 529 0
AFLR4 : Nodes, Trias,Quads= 178 283 0
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Trias,Quads= 233 409 0
AFLR4 : Nodes, Trias,Quads= 189 321 0
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Trias,Quads= 292 511 0
AFLR4 : Nodes, Trias,Quads= 174 275 0
AFLR4 : Generate optimal mesh on surface definition 5
AFLR2 : Nodes, Trias,Quads= 9 10 0
AFLR4 : Nodes, Trias,Quads= 6 4 0
AFLR4 : Generate optimal mesh on surface definition 6
AFLR2 : Nodes, Trias,Quads= 241 424 0
AFLR4 : Nodes, Trias,Quads= 202 346 0
AFLR4 : Generate optimal mesh on surface definition 7
AFLR2 : Nodes, Trias,Quads= 302 531 0
AFLR4 : Nodes, Trias,Quads= 177 281 0
AFLR4 : Generate optimal mesh on surface definition 8
AFLR2 : Nodes, Trias,Quads= 235 413 0
AFLR4 : Nodes, Trias,Quads= 189 321 0
AFLR4 : Generate optimal mesh on surface definition 9
AFLR2 : Nodes, Trias,Quads= 293 513 0
AFLR4 : Nodes, Trias,Quads= 173 273 0
AFLR4 : Generate optimal mesh on surface definition 10
AFLR2 : Nodes, Trias,Quads= 9 10 0
AFLR4 : Nodes, Trias,Quads= 6 4 0
AFLR4 : Generate optimal mesh on surface definition 11
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 12
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 13
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 14
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 15
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 16
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes,Faces,BEdges= 1238 2468 542
AFLR4 : Curvature BG Surface Grid Generation
AFLR4 : Nodes, Faces = 1238 2468
AFLR4 : Surface Grid Generation
AFLR4 : Generate optimal mesh on surface definition 1
AFLR2 : Nodes, Trias,Quads= 1695 3170 0
AFLR4 : Nodes, Trias,Quads= 1371 2522 0
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Trias,Quads= 3139 5972 0
AFLR4 : Nodes, Trias,Quads= 1805 3304 0
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Trias,Quads= 1597 2983 0
AFLR4 : Nodes, Trias,Quads= 1311 2411 0
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Trias,Quads= 3114 5923 0
AFLR4 : Nodes, Trias,Quads= 1786 3267 0
AFLR4 : Generate optimal mesh on surface definition 5
AFLR2 : Nodes, Trias,Quads= 36 46 0
AFLR4 : Nodes, Trias,Quads= 24 22 0
AFLR4 : Generate optimal mesh on surface definition 6
AFLR2 : Nodes, Trias,Quads= 1691 3162 0
AFLR4 : Nodes, Trias,Quads= 1376 2532 0
AFLR4 : Generate optimal mesh on surface definition 7
AFLR2 : Nodes, Trias,Quads= 3162 6018 0
AFLR4 : Nodes, Trias,Quads= 1802 3298 0
AFLR4 : Generate optimal mesh on surface definition 8
AFLR2 : Nodes, Trias,Quads= 1600 2989 0
AFLR4 : Nodes, Trias,Quads= 1326 2441 0
AFLR4 : Generate optimal mesh on surface definition 9
AFLR2 : Nodes, Trias,Quads= 3109 5913 0
AFLR4 : Nodes, Trias,Quads= 1784 3263 0
AFLR4 : Generate optimal mesh on surface definition 10
AFLR2 : Nodes, Trias,Quads= 36 46 0
AFLR4 : Nodes, Trias,Quads= 24 22 0
AFLR4 : Generate optimal mesh on surface definition 11
AFLR2 : Nodes, Trias,Quads= 12 14 0
AFLR4 : Nodes, Trias,Quads= 8 6 0
AFLR4 : Generate optimal mesh on surface definition 12
AFLR2 : Nodes, Trias,Quads= 12 14 0
AFLR4 : Nodes, Trias,Quads= 8 6 0
AFLR4 : Generate optimal mesh on surface definition 13
AFLR2 : Nodes, Trias,Quads= 12 14 0
AFLR4 : Nodes, Trias,Quads= 8 6 0
AFLR4 : Generate optimal mesh on surface definition 14
AFLR2 : Nodes, Trias,Quads= 12 14 0
AFLR4 : Nodes, Trias,Quads= 8 6 0
AFLR4 : Generate optimal mesh on surface definition 15
AFLR2 : Nodes, Trias,Quads= 12 14 0
AFLR4 : Nodes, Trias,Quads= 8 6 0
AFLR4 : Generate optimal mesh on surface definition 16
AFLR2 : Nodes, Trias,Quads= 12 14 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= 11563 23118 2164
OVERALL : CPU Time = 0.307 seconds
Body 1 (of 2)
Number of nodes = 11543
Number of elements = 23082
Number of triangle elements = 23082
Number of quadrilateral elements = 0
Body 2 (of 2)
Number of nodes = 20
Number of elements = 36
Number of triangle elements = 36
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 11563
Total number of elements = 23118
Total number of triangle elements = 23118
Total number of quadrilateral elements = 0
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = leftWing, index = 1
Name = riteWing, index = 2
Name = Farfield, index = 3
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Wing, index = 1
Name = Farfield, index = 2
Getting volume mesh
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
UG PARAM : mrecm = 3
UG PARAM : mrecqm = 3
UG PARAM : mpfrmt = 0
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.18.1
AFLR2 : Version Date 06/11/24 @ 05:52PM
AFLR2 : Compile OS Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR2 : Compile Date 06/11/24 @ 06:33PM
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 11.5.15
AFLR4 : Version Date 07/19/24 @ 07:04PM
AFLR4 : Compile OS Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR4 : Compile Date 07/19/24 @ 07:42PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.27
EGADS : OpenCASCADE Version 7.8.1
EGADS : ---------------------------------------
EGADS : EGADS CAD Geometry Setup
EGADS : Model has 2 Active Bodies
EGADS : Body 0 is a SolidBody
EGADS : Body 0 has 1 Shells
EGADS : Body 0 has 10 Faces
EGADS : Body 0 has 18 Edges
EGADS : Body 0 has 10 Loops
EGADS : Body 0 has 10 Nodes
EGADS : Body 1 is a SolidBody
EGADS : Body 1 has 1 Shells
EGADS : Body 1 has 6 Faces
EGADS : Body 1 has 12 Edges
EGADS : Body 1 has 6 Loops
EGADS : Body 1 has 8 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 0.5 1 2 3 6
EGADS : 2 Yes 0 0 1 0.5 1 1 4 5
EGADS : 3 Yes 0 0 1 0.5 1 1 4 8
EGADS : 4 Yes 0 0 1 0.5 1 2 3 5
EGADS : 5 Yes 0 0 1 0.5 1 2 4
EGADS : 6 Yes 0 0 1 0.5 1 1 7 8
EGADS : 7 Yes 0 0 1 0.5 1 6 9 10
EGADS : 8 Yes 0 0 1 0.5 1 3 6 9
EGADS : 9 Yes 0 0 1 0.5 1 7 8 10
EGADS : 10 Yes 0 0 1 0.5 1 7 9
EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16
EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16
EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16
EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16
EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14
EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14
EGADS : Face Edges Information
EGADS : Face Edges
EGADS : 1 -1 2 3 -4
EGADS : 2 -5 4 6 -7
EGADS : 3 -3 8 1 -9
EGADS : 4 -6 9 5 -10
EGADS : 5 7 10
EGADS : 6 11 13 -12 -2
EGADS : 7 14 16 -15 -13
EGADS : 8 12 17 -11 -8
EGADS : 9 15 18 -14 -17
EGADS : 10 -16 -18
EGADS : 11 19 20 -21 -22
EGADS : 12 -23 26 25 -24
EGADS : 13 27 23 -28 -19
EGADS : 14 -29 21 30 -25
EGADS : 15 22 29 -26 -27
EGADS : 16 -20 28 24 -30
EGADS : Face Loops Information
EGADS : Face Loops
EGADS : 1 1
EGADS : 2 2
EGADS : 3 3
EGADS : 4 4
EGADS : 5 5
EGADS : 6 6
EGADS : 7 7
EGADS : 8 8
EGADS : 9 9
EGADS : 10 10
EGADS : 11 11
EGADS : 12 12
EGADS : 13 13
EGADS : 14 14
EGADS : 15 15
EGADS : 16 16
EGADS : Loop Edges Information
EGADS : Loop Active Edges
EGADS : 1 Yes -1 2 3 -4
EGADS : 2 Yes -5 4 6 -7
EGADS : 3 Yes -3 8 1 -9
EGADS : 4 Yes -6 9 5 -10
EGADS : 5 Yes 7 10
EGADS : 6 Yes 11 13 -12 -2
EGADS : 7 Yes 14 16 -15 -13
EGADS : 8 Yes 12 17 -11 -8
EGADS : 9 Yes 15 18 -14 -17
EGADS : 10 Yes -16 -18
EGADS : 11 Yes 19 20 -21 -22
EGADS : 12 Yes -23 26 25 -24
EGADS : 13 Yes 27 23 -28 -19
EGADS : 14 Yes -29 21 30 -25
EGADS : 15 Yes 22 29 -26 -27
EGADS : 16 Yes -20 28 24 -30
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 1 2 1 1 3
EGADS : 2 0 Yes 1 3 1 1 6
EGADS : 3 0 Yes 3 4 1 1 3
EGADS : 4 0 Yes 2 4 1 1 2
EGADS : 5 0 Yes 2 5 1 2 4
EGADS : 6 0 Yes 4 6 1 2 4
EGADS : 7 0 Yes 5 6 1 2 5
EGADS : 8 0 Yes 3 1 1 3 8
EGADS : 9 0 Yes 4 2 1 3 4
EGADS : 10 0 Yes 6 5 1 4 5
EGADS : 11 0 Yes 1 7 1 6 8
EGADS : 12 0 Yes 3 8 1 6 8
EGADS : 13 0 Yes 7 8 1 6 7
EGADS : 14 0 Yes 7 9 1 7 9
EGADS : 15 0 Yes 8 10 1 7 9
EGADS : 16 0 Yes 9 10 1 7 10
EGADS : 17 0 Yes 8 7 1 8 9
EGADS : 18 0 Yes 10 9 1 9 10
EGADS : 19 1 Yes 12 11 NA 11 13
EGADS : 20 1 Yes 11 13 NA 11 16
EGADS : 21 1 Yes 14 13 NA 11 14
EGADS : 22 1 Yes 12 14 NA 11 15
EGADS : 23 1 Yes 16 15 NA 12 13
EGADS : 24 1 Yes 15 17 NA 12 16
EGADS : 25 1 Yes 18 17 NA 12 14
EGADS : 26 1 Yes 16 18 NA 12 15
EGADS : 27 1 Yes 12 16 NA 13 15
EGADS : 28 1 Yes 11 15 NA 13 16
EGADS : 29 1 Yes 14 18 NA 14 15
EGADS : 30 1 Yes 13 17 NA 14 16
EGADS : Node Information
EGADS : Node Active Coordinates
EGADS : 1 Yes 97.2007855 0 0
EGADS : 2 Yes 97.9335611 0 0
EGADS : 3 Yes 50 0 0
EGADS : 4 Yes 75.3047874 0 0
EGADS : 5 Yes 123.552357 0 4.7180639
EGADS : 6 Yes 118.391317 0 3.99272703
EGADS : 7 Yes 97.9335611 36.1389817 0
EGADS : 8 Yes 75.3047874 36.1389817 0
EGADS : 9 Yes 123.552357 97.6729236 4.7180639
EGADS : 10 Yes 118.391317 97.6729236 3.99272703
EGADS : 11 Yes 0 0 1951.57774
EGADS : 12 Yes 0 0 0
EGADS : 13 Yes 0 1953.45847 1951.57774
EGADS : 14 Yes 0 1953.45847 0
EGADS : 15 Yes 2040.21562 0 1951.57774
EGADS : 16 Yes 2040.21562 0 0
EGADS : 17 Yes 2040.21562 1953.45847 1951.57774
EGADS : 18 Yes 2040.21562 1953.45847 0
EGADS : Face and Edge Match Information
EGADS : No Face Matches Found
AFLR4 : Surface Mesh Spacing Setup
AFLR4 : Max Bounding Box Length = 3906.92
AFLR4 : Min Bounding Box Length = 3906.92
AFLR4 : Max Ref Bounding Box Length = 195.346
AFLR4 : Min Ref Bounding Box Length = 13.1976
AFLR4 : Reference Length = 13.1976
AFLR4 : BL Thickness = 0
AFLR4 : FarField Spacing = 428.309
AFLR4 : Abs Min Surf Spacing = 0.032994
AFLR4 : Min Surf Spacing = 0.065988
AFLR4 : Max Surf Spacing = 1.31976
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
AFLR4 : 2 CAD geometry 0 STD
AFLR4 : 3 CAD geometry 0 STD
AFLR4 : 4 CAD geometry 0 STD
AFLR4 : 5 CAD geometry 0 STD
AFLR4 : 6 CAD geometry 0 STD
AFLR4 : 7 CAD geometry 0 STD
AFLR4 : 8 CAD geometry 0 STD
AFLR4 : 9 CAD geometry 0 STD
AFLR4 : 10 CAD geometry 0 STD
AFLR4 : 11 CAD geometry 0 FARFIELD
AFLR4 : 12 CAD geometry 0 FARFIELD
AFLR4 : 13 CAD geometry 0 FARFIELD
AFLR4 : 14 CAD geometry 0 FARFIELD
AFLR4 : 15 CAD geometry 0 FARFIELD
AFLR4 : 16 CAD geometry 0 FARFIELD
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 : Define CAD surface definition 10
AFLR4 : Define CAD surface definition 11
AFLR4 : Define CAD surface definition 12
AFLR4 : Define CAD surface definition 13
AFLR4 : Define CAD surface definition 14
AFLR4 : Define CAD surface definition 15
AFLR4 : Define CAD surface definition 16
AFLR43 : INPUT SURFACE MESH FROM TESS
AFLR43 : Quad Surface Faces= 0
AFLR43 : Tria Surface Faces= 23118
AFLR43 : Nodes = 11563
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
UG PARAM : mrecm = 3
UG PARAM : mrecqm = 3
UG PARAM : mpfrmt = 0
AFLR3 : ---------------------------------------
AFLR3 : AFLR3 LIBRARY
AFLR3 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR3 : TETRAHEDRAL GRID GENERATOR
AFLR3 : Version Number 16.32.50
AFLR3 : Version Date 10/31/23 @ 06:31PM
AFLR3 : Compile OS Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR3 : Compile Date 03/08/24 @ 01:03AM
AFLR3 : Copyright 1994-2021, D.L. Marcum
AFLR3 : ---------------------------------------
AFLR3 IC : INPUT SURFACE GRID CHECK
AFLR3 IC : Nodes, Elements = 11563 0
UG3 : Boundary Conditions
UG3 : B-Face ID Boundary Condition
UG3 : 1 Solid
UG3 : 2 Solid
UG3 : 3 Solid
UG3 : 4 Solid
UG3 : 5 Solid
UG3 : 6 Solid
UG3 : 7 Solid
UG3 : 8 Solid
UG3 : 9 Solid
UG3 : 10 Solid
UG3 : 11 FarField
UG3 : 12 FarField
UG3 : 13 FarField
UG3 : 14 FarField
UG3 : 15 FarField
UG3 : 16 FarField
AFLR3 : CPU Time = 0.027 seconds
AFLR3 IG : INITIAL VOLUME GRID GENERATION
AFLR3 IG : Nodes, Elements = 11563 0
AFLR3 IG : Nodes, Elements = 8 10
AFLR3 IG : Nodes, Elements = 2314 16714
AFLR3 IG : Nodes, Elements = 4628 33743
AFLR3 IG : Nodes, Elements = 6942 53624
AFLR3 IG : Nodes, Elements = 9256 74436
AFLR3 IG : Nodes, Elements = 11570 95705
AFLR3 IG : Nodes, Elements = 11570 95484
AFLR3 IG : Nodes, Elements = 11563 61781
AFLR3 IG : Nodes, Elements = 11563 61866
AFLR3 IG : Nodes, Elements = 11563 39406
AFLR3 IG : Nodes, Elements = 11563 34648
AFLR3 : CPU Time = 0.567 seconds
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
AFLR3 GG : Nodes, Elements = 11563 34648
AFLR3 GG : Nodes, Elements = 16540 49868
AFLR3 GG : Nodes, Elements = 16540 71064
AFLR3 GG : Nodes, Elements = 16540 65866
AFLR3 GG : Nodes, Elements = 20460 78248
AFLR3 GG : Nodes, Elements = 20460 93032
AFLR3 GG : Nodes, Elements = 20460 87608
AFLR3 GG : Nodes, Elements = 24762 101165
AFLR3 GG : Nodes, Elements = 24762 118161
AFLR3 GG : Nodes, Elements = 24762 112637
AFLR3 GG : Nodes, Elements = 29409 126844
AFLR3 GG : Nodes, Elements = 29409 145554
AFLR3 GG : Nodes, Elements = 29409 139920
AFLR3 GG : Nodes, Elements = 34333 154947
AFLR3 GG : Nodes, Elements = 34333 174455
AFLR3 GG : Nodes, Elements = 34333 168984
AFLR3 GG : Nodes, Elements = 39311 184113
AFLR3 GG : Nodes, Elements = 39311 203835
AFLR3 GG : Nodes, Elements = 39311 198641
AFLR3 GG : Nodes, Elements = 44294 213772
AFLR3 GG : Nodes, Elements = 44294 233414
AFLR3 GG : Nodes, Elements = 44294 228210
AFLR3 GG : Nodes, Elements = 49233 243197
AFLR3 GG : Nodes, Elements = 49233 262591
AFLR3 GG : Nodes, Elements = 49233 257486
AFLR3 GG : Nodes, Elements = 54058 272070
AFLR3 GG : Nodes, Elements = 54058 291031
AFLR3 GG : Nodes, Elements = 54058 286070
AFLR3 GG : Nodes, Elements = 58813 300428
AFLR3 GG : Nodes, Elements = 58813 318814
AFLR3 GG : Nodes, Elements = 58813 314152
AFLR3 GG : Nodes, Elements = 63545 328403
AFLR3 GG : Nodes, Elements = 63545 346723
AFLR3 GG : Nodes, Elements = 63545 342173
AFLR3 GG : Nodes, Elements = 68179 356114
AFLR3 GG : Nodes, Elements = 68179 374204
AFLR3 GG : Nodes, Elements = 68179 369759
AFLR3 GG : Nodes, Elements = 72701 383355
AFLR3 GG : Nodes, Elements = 72701 400844
AFLR3 GG : Nodes, Elements = 72701 396485
AFLR3 GG : Nodes, Elements = 76974 409326
AFLR3 GG : Nodes, Elements = 76974 426108
AFLR3 GG : Nodes, Elements = 76974 421814
AFLR3 GG : Nodes, Elements = 81140 434332
AFLR3 GG : Nodes, Elements = 81140 450481
AFLR3 GG : Nodes, Elements = 81140 446570
AFLR3 GG : Nodes, Elements = 84975 458091
AFLR3 GG : Nodes, Elements = 84975 473033
AFLR3 GG : Nodes, Elements = 84975 469311
AFLR3 GG : Nodes, Elements = 88723 480573
AFLR3 GG : Nodes, Elements = 88723 495197
AFLR3 GG : Nodes, Elements = 88723 491547
AFLR3 GG : Nodes, Elements = 92276 502214
AFLR3 GG : Nodes, Elements = 92276 516130
AFLR3 GG : Nodes, Elements = 92276 512639
AFLR3 GG : Nodes, Elements = 95577 522551
AFLR3 GG : Nodes, Elements = 95577 535310
AFLR3 GG : Nodes, Elements = 95577 532228
AFLR3 GG : Nodes, Elements = 98606 541325
AFLR3 GG : Nodes, Elements = 98606 553258
AFLR3 GG : Nodes, Elements = 98606 550262
AFLR3 GG : Nodes, Elements = 101367 558552
AFLR3 GG : Nodes, Elements = 101367 569495
AFLR3 GG : Nodes, Elements = 101367 566686
AFLR3 GG : Nodes, Elements = 103827 574069
AFLR3 GG : Nodes, Elements = 103827 583741
AFLR3 GG : Nodes, Elements = 103827 581349
AFLR3 GG : Nodes, Elements = 105986 587827
AFLR3 GG : Nodes, Elements = 105986 596375
AFLR3 GG : Nodes, Elements = 105986 594113
AFLR3 GG : Nodes, Elements = 107829 599649
AFLR3 GG : Nodes, Elements = 107829 606900
AFLR3 GG : Nodes, Elements = 107829 604997
AFLR3 GG : Nodes, Elements = 109360 609591
AFLR3 GG : Nodes, Elements = 109360 615722
AFLR3 GG : Nodes, Elements = 109360 614147
AFLR3 GG : Nodes, Elements = 110594 617849
AFLR3 GG : Nodes, Elements = 110594 622977
AFLR3 GG : Nodes, Elements = 110594 621500
AFLR3 GG : Nodes, Elements = 111589 624486
AFLR3 GG : Nodes, Elements = 111589 628573
AFLR3 GG : Nodes, Elements = 111589 627403
AFLR3 GG : Nodes, Elements = 112393 629815
AFLR3 GG : Nodes, Elements = 112393 633084
AFLR3 GG : Nodes, Elements = 112393 632177
AFLR3 GG : Nodes, Elements = 112970 633910
AFLR3 GG : Nodes, Elements = 112970 636314
AFLR3 GG : Nodes, Elements = 112970 635572
AFLR3 GG : Nodes, Elements = 113416 636911
AFLR3 GG : Nodes, Elements = 113416 638834
AFLR3 GG : Nodes, Elements = 113416 638222
AFLR3 GG : Nodes, Elements = 113747 639215
AFLR3 GG : Nodes, Elements = 113747 640649
AFLR3 GG : Nodes, Elements = 113747 640182
AFLR3 GG : Nodes, Elements = 114028 641026
AFLR3 GG : Nodes, Elements = 114028 642202
AFLR3 GG : Nodes, Elements = 114028 641827
AFLR3 GG : Nodes, Elements = 114231 642436
AFLR3 GG : Nodes, Elements = 114231 643375
AFLR3 GG : Nodes, Elements = 114231 643009
AFLR3 GG : Nodes, Elements = 114420 643577
AFLR3 GG : Nodes, Elements = 114420 644398
AFLR3 GG : Nodes, Elements = 114420 644122
AFLR3 GG : Nodes, Elements = 114567 644563
AFLR3 GG : Nodes, Elements = 114567 645259
AFLR3 GG : Nodes, Elements = 114567 645015
AFLR3 GG : Nodes, Elements = 114693 645393
AFLR3 GG : Nodes, Elements = 114693 645966
AFLR3 GG : Nodes, Elements = 114693 645765
AFLR3 GG : Nodes, Elements = 114796 646074
AFLR3 GG : Nodes, Elements = 114796 646522
AFLR3 GG : Nodes, Elements = 114796 646358
AFLR3 GG : Nodes, Elements = 114846 646508
AFLR3 GG : Nodes, Elements = 114846 646760
AFLR3 GG : Nodes, Elements = 114846 646657
AFLR3 GG : Nodes, Elements = 114874 646741
AFLR3 GG : Nodes, Elements = 114874 646888
AFLR3 GG : Nodes, Elements = 114874 646813
AFLR3 GG : Nodes, Elements = 114880 646831
AFLR3 GG : Nodes, Elements = 114880 646860
AFLR3 GG : Nodes, Elements = 114880 646844
AFLR3 GG : Nodes, Elements = 114881 646847
AFLR3 GG : Nodes, Elements = 114881 646855
AFLR3 GG : Nodes, Elements = 114881 646852
AFLR3 GG : Nodes, Elements = 114888 646873
AFLR3 GG : Nodes, Elements = 114888 646895
AFLR3 GG : Nodes, Elements = 114888 646889
AFLR3 : CPU Time = 12.118 seconds
AFLR3 QI : QUALITY IMPROVEMENT
AFLR3 QI : Nodes, Elements = 114888 646889
AFLR3 QI : Nodes, Elements = 114166 642814
AFLR3 QI : Nodes, Elements = 114049 642130
AFLR3 QI : Nodes, Elements = 114029 642009
AFLR3 QI : Nodes, Elements = 114025 641984
AFLR3 QI : Nodes, Elements = 114023 641971
AFLR3 QI : Nodes, Elements = 114023 645235
AFLR3 QI : Nodes, Elements = 114023 641671
AFLR3 QI : Nodes, Elements = 114023 640227
AFLR3 QI : Nodes, Elements = 114023 642983
AFLR3 QI : Nodes, Elements = 114023 640284
AFLR3 QI : Nodes, Elements = 114023 640131
AFLR3 QI : Nodes, Elements = 114023 642727
AFLR3 QI : Nodes, Elements = 114023 640237
AFLR3 QI : Nodes, Elements = 114023 640116
AFLR3 QI : Nodes, Elements = 114023 642661
AFLR3 QI : Nodes, Elements = 114023 640221
AFLR3 QI : Nodes, Elements = 114023 640123
AFLR3 QI : Nodes, Elements = 114023 642641
AFLR3 QI : Nodes, Elements = 114023 640218
AFLR3 QI : Nodes, Elements = 114023 640114
AFLR3 QI : Nodes, Elements = 114023 640113
AFLR3 QI : Nodes, Elements = 114029 640142
AFLR3 QI : Nodes, Elements = 114029 642714
AFLR3 QI : Nodes, Elements = 114029 640274
AFLR3 QI : Nodes, Elements = 114029 640155
AFLR3 QI : Nodes, Elements = 114029 642666
AFLR3 QI : Nodes, Elements = 114029 640252
AFLR3 QI : Nodes, Elements = 114029 640157
AFLR3 : CPU Time = 5.007 seconds
AFLR3 QRG: QUALITY GRID RE-GENERATION
AFLR3 QRG: Nodes, Elements = 114029 640157
AFLR3 QRG: Nodes, Elements = 114035 640193
AFLR3 QRG: Nodes, Elements = 114062 640345
AFLR3 : CPU Time = 0.099 seconds
AFLR3 : DONE
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 640345
UG3 : Min, Max Ang = 0.008181 180
UG3 : Average Angle = 70.2
UG3 : No. Angle>160.0 = 101
UG3 : No. Angle>179.9 = 5
UG3 : VOL CHECK
UG3 : Total-Volume = 5.96e+10
UG3 : No. Tet Elems = 640345
UG3 : Min Vol = 1.16e-05
UG3 : Average Vol = 9.31e+04
UG3 : Total-Tet-Vol = 5.96e+10
UG3 : No. Vol<TOL = 0
UG3 : Q VOL-LENGTH-RATIO CHECK
2/3 2
UG3 : Q = c * Vol / sum( L )
UG3 : 0 <= Q <= 1
UG3 : No. Tet Elems = 640345
UG3 : Min, Max Q = 0.000234 1
UG3 : Average Q = 0.858
UG3 : No. Q< 0.1 = 229
UG3 : No. Q< 0.01 = 10
OVERALL : CPU Time = 18.560 seconds
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 640345
UG3 : Min, Max Ang = 0.008181 180
UG3 : Average Angle = 70.2
UG3 : No. Angle>160.0 = 101
UG3 : No. Angle>179.9 = 5
UG3 : VOL CHECK
UG3 : Total-Volume = 5.96e+10
UG3 : No. Tet Elems = 640345
UG3 : Min Vol = 1.16e-05
UG3 : Average Vol = 9.31e+04
UG3 : Total-Tet-Vol = 5.96e+10
UG3 : No. Vol<TOL = 0
UG3 : Q VOL-LENGTH-RATIO CHECK
2/3 2
UG3 : Q = c * Vol / sum( L )
UG3 : 0 <= Q <= 1
UG3 : Note that L includes scaling for BL-aspect=ratio
UG3 : No. Tet Elems = 640345
UG3 : Min, Max Q = 0.000717 1
UG3 : Average Q = 0.842
UG3 : No. Q< 0.1 = 30
UG3 : No. Q< 0.01 = 9
UG3 : CPU Time = 0.000 seconds
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.27
EGADS : OpenCASCADE Version 7.8.1
EGADS : ---------------------------------------
EGADS : CREATE EGADS TESS FROM AFLR3 DATA
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 1
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 2
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 3
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 4
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 5
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 6
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 7
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 8
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 9
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 10
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 11
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 12
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 13
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 14
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 15
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 16
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 17
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 18
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 1
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 2
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 3
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 4
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 5
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 6
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 7
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 8
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 9
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 10
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 19
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 20
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 21
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 22
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 23
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 24
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 25
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 26
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 27
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 28
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 29
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 30
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 11
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 12
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 13
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 14
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 15
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 16
EGADS : EGADS TESS CREATED
EGADS : CHECK TESS FACE NODE MAP
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 1
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 2
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 3
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 4
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 5
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 6
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 7
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 8
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 9
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 10
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 11
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 12
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 13
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 14
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 15
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 16
Volume mesh:
Number of nodes = 114062
Number of elements = 663463
Number of triangles = 23118
Number of quadrilatarals = 0
Number of tetrahedrals = 640345
Number of pyramids = 0
Number of prisms = 0
Number of hexahedrals = 0
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wing
Done getting CFD boundary conditions
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Harrier (8.0.1)"
==> Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.1 "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 2012-2024, 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 4240 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 195.346 m.
Reference origin for moment evaluation is (55.4263, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.
Surface(s) plotted in the output file: BC_1.
Surface(s) affected by the design variables: BC_1.
Input mesh file name: ../aflr3/aflr3_CAPS.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| TECPLOT| 250|
| SURFACE_TECPLOT| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface file name: surface_flow_aeroelasticIterative.
Volume file name: flow_aeroelasticIterative.
Restart file name: restart_flow_aeroelasticIterative.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| 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.
114062 grid points.
640345 volume elements.
2 surface markers.
23082 boundary elements in index 0 (Marker = BC_1).
36 boundary elements in index 1 (Marker = BC_2).
640345 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: 5.96352e+10.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 29.8369. Mean K: 1.54053. Standard deviation K: 3.02442.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 3.92789| 85.6007|
| CV Face Area Aspect Ratio| 1.02637| 24101|
| CV Sub-Volume Ratio| 1.0443| 262904|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 114062| 1/1.00| 10|
| 1| 18759| 1/6.08| 8.21828|
| 2| 2871| 1/6.53| 6.59396|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 97.6729 m.
Wetted area = 8661.82 m^2.
Area projection in the x-plane = 677.811 m^2, y-plane = 441.377 m^2, z-plane = 4150.8 m^2.
Max. coordinate in the x-direction = 123.552 m, y-direction = 97.6729 m, z-direction = 4.71806 m.
Min. coordinate in the x-direction = 50 m, y-direction = -97.6729 m, z-direction = -8.47948 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 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| 5.7081e+00| 0.790080| 2.949073| 2.686336| 6.259186| -0.780968|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.6061e+00| 3.380625| 5.793050| 5.596559| 8.842120| -0.609181|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.4804e+00| 5.265484| 7.766507| 7.475054| 10.742276| -7.199792|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 5.3923e+00| 6.857032| 9.473371| 9.098630| 12.297480| -7.568221|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 5.1950e+00| 6.672661| 8.971551| 8.964740| 12.065644| -6.974150|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 6.67266| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticIterative.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|CSV file |surface_flow_aeroelasticIterative.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary |flow_aeroelasticIterative.szplt |
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary surface |surface_flow_aeroelasticIterative.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
+-----------------------------------------------------------------------+
Warning: there are 435 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 SU2 post-analysis...
==> Running ASTROS pre-analysis...
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 2
Name = wingSpar1, index = 1
Name = wingSpar2, index = 2
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 425
Number of elements = 482
Number of triangle elements = 0
Number of quadrilateral elements = 482
----------------------------
Total number of nodes = 425
Total number of elements = 482
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 4
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Name = leftPointLoad, index = 3
Name = ritePointLoad, index = 4
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = leftWingSkin, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = wingSpar2, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 425
Number of elements = 482
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 482
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 1
Load name - pressureAero
No "groupName" specified for Load tuple pressureAero, going to use load name
Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 11543
CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
Rank 0: src = 4.027490e+12, tgt = 4.027490e+12, diff = 1.704907e+03
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 11543
CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
Rank 0: src = 4.913399e+12, tgt = 4.913399e+12, diff = 5.627539e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 11543
CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
Rank 0: src = 1.372387e+09, tgt = 1.372386e+09, diff = 5.254404e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 11543
CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
Rank 0: src = 1.852844e+09, tgt = 1.852845e+09, diff = 7.613525e+02
Extracting external pressure loads from data transfer....
TransferName = upperWing
Number of Elements = 98 (total = 98)
Extracting external pressure loads from data transfer....
TransferName = lowerWing
Number of Elements = 98 (total = 196)
Extracting external pressure loads from data transfer....
TransferName = leftTip
Number of Elements = 17 (total = 213)
Extracting external pressure loads from data transfer....
TransferName = riteTip
Number of Elements = 17 (total = 230)
Writing Astros grid and connectivity file (in free field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS......
==> Running ASTROS post-analysis...
==> Running SU2 pre-analysis...
Writing boundary flags
- bcProps.surfaceProp[0].surfaceType = 3
- bcProps.surfaceProp[1].surfaceType = 1
Done boundary flags
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Harrier (8.0.1)"
==> Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.1 "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 2012-2024, 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_CAPS.su2
---------------- Grid deformation parameters ( Zone 0 ) ----------------
Grid deformation using a linear elasticity method.
-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: ../aflr3/aflr3_CAPS.su2.
Cell stiffness scaled by distance to nearest solid surface.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| BC_2|
+-----------------------------------------------------------------------+
Three dimensional problem.
114062 grid points.
640345 volume elements.
2 surface markers.
23082 boundary elements in index 0 (Marker = BC_1).
36 boundary elements in index 1 (Marker = BC_2).
640345 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: 5.96352e+10.
Info: Ignoring the following volume output fields/groups:
SOLUTION
Volume output fields: COORDINATES
Info: Ignoring the following screen output fields:
RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME
Info: Ignoring the following history output groups:
RMS_RES, AERO_COEFF
History output group(s): ITER, TIME_DOMAIN, WALL_TIME
Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive.
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
--------------------- Surface grid deformation (ZONE 0) -----------------
Performing the deformation of the surface grid.
Updating the surface coordinates from the input file.
------------------- Volumetric grid deformation (ZONE 0) ----------------
Performing the deformation of the volumetric grid.
WARNING: Convexity is not checked for 3D elements (issue #1171).
Completed in 173.755209 seconds on 1 core.
----------------------- Write deformed grid files -----------------------
|SU2 mesh |../aflr3/aflr3_CAPS.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 8.0.1 "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 2012-2024, 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 4240 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 195.346 m.
Reference origin for moment evaluation is (55.4263, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.
Surface(s) plotted in the output file: BC_1.
Surface(s) affected by the design variables: BC_1.
Input mesh file name: ../aflr3/aflr3_CAPS.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| TECPLOT| 250|
| SURFACE_TECPLOT| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface file name: surface_flow_aeroelasticIterative.
Volume file name: flow_aeroelasticIterative.
Restart file name: restart_flow_aeroelasticIterative.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| 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.
114062 grid points.
640345 volume elements.
2 surface markers.
23082 boundary elements in index 0 (Marker = BC_1).
36 boundary elements in index 1 (Marker = BC_2).
640345 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 327455 TETRAHEDRON volume elements.
There has been a re-orientation of 8188 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 6.85691e+10.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 44.3084. Mean K: 1.13837. Standard deviation K: 2.16809.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 0.299798| 74.6917|
| CV Face Area Aspect Ratio| 1.07032| 77446.5|
| CV Sub-Volume Ratio| 1.07512| 1.95773e+07|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 114062| 1/1.00| 10|
| 1| 18687| 1/6.1| 8.20775|
| 2| 2845| 1/6.57| 6.574|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 209.21 m.
Wetted area = 2.10834e+07 m^2.
Area projection in the x-plane = 1.02564e+07 m^2, y-plane = 1.14378e+06 m^2, z-plane = 980325 m^2.
Max. coordinate in the x-direction = 445.294 m, y-direction = 209.21 m, z-direction = 204.707 m.
Min. coordinate in the x-direction = 22.5929 m, y-direction = -265.325 m, z-direction = -3436.06 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 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| 4.9087e+00| 6.090260| 9.056309| 9.101235| 11.559366| 0.096017|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.3889e+00| 6.257565| 8.950361| 9.026252| 11.684198| 0.094460|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.8405e+00| 6.353118| 9.006642| 9.048633| 11.847708| 0.096403|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 5.9532e+00| 6.485125| 8.999709| 9.085350| 11.934847| 0.097469|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 5.9861e+00| 6.413024| 8.976805| 9.055619| 11.857858| 0.098243|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 6.41302| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticIterative.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|CSV file |surface_flow_aeroelasticIterative.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary |flow_aeroelasticIterative.szplt |
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary surface |surface_flow_aeroelasticIterative.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
+-----------------------------------------------------------------------+
Warning: there are 1028 non-physical points in the solution.
Warning: 642 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 SU2 post-analysis...
==> Running ASTROS pre-analysis...
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 11543
CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
Rank 0: src = 1.958562e+12, tgt = 1.958562e+12, diff = 1.088420e+03
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 11543
CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
Rank 0: src = 1.846952e+12, tgt = 1.846952e+12, diff = 7.846191e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 11543
CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
Rank 0: src = 4.501598e+08, tgt = 4.501648e+08, diff = 5.048298e+03
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 11543
CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
Rank 0: src = 3.574097e+08, tgt = 3.574117e+08, diff = 1.973913e+03
Extracting external pressure loads from data transfer....
TransferName = upperWing
Number of Elements = 98 (total = 98)
Extracting external pressure loads from data transfer....
TransferName = lowerWing
Number of Elements = 98 (total = 196)
Extracting external pressure loads from data transfer....
TransferName = leftTip
Number of Elements = 17 (total = 213)
Extracting external pressure loads from data transfer....
TransferName = riteTip
Number of Elements = 17 (total = 230)
Writing Astros grid and connectivity file (in free field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS......
==> Running ASTROS post-analysis...
real 5m51.269s
user 6m16.984s
sys 6m29.159s
+ status=0
+ set +x
=================================================
data/session10/2_aeroelastic_Iterative_SU2_Astros.py passed (as expected)
=================================================
*************************************************
*************************************************
=================================================
Did not run examples for:
session08 fun3d
session09 nastran
session11 fun3d+astros
=================================================
All tests pass!
[Execution node] check if [reynolds] is in [[windows10x64]]
Run condition [Execution node ] preventing perform for step [Execute Windows batch command]
[GNU C Compiler (gcc)] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/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_RegCaps/7.8/CAPS/training/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/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_RegCaps/7.8/CAPS/training/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] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/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] No valid reference build found
[Static Analysis] All reported issues will be considered outstanding
[Static Analysis] No quality gates have been set - skipping
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_RegCaps/CASREV=7.8,ESPTEST=CAPS/training,ESP_ARCH=LINUX64,buildnode=reynolds #681'.
[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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