Skipping 4,291 KB..
Full Log| 0| 820508| 1/1.00| 10|
| 1| 134785| 1/6.09| 8.21506|
| 2| 20535| 1/6.56| 6.58142|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 97.6729 m.
Wetted 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| 4.9700e+01| 0.380851| 2.660758| 2.133847| 5.863696| -0.406802|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 4.8451e+01| 3.089553| 5.521554| 5.335357| 8.558356| -0.099438|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.9761e+01| 4.810028| 7.316610| 7.041831| 10.290152| 12.937512|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.3778e+01| 6.565243| 8.879480| 8.945823| 11.976242| -314.032672|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.0119e+01| 7.059342| 9.492882| 9.317846| 12.505843| 3.580064|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 2.7890e+01| 7.799694| 10.546869| 10.457609| 13.387376| -5.083226|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 2.6130e+01| 7.297248| 9.986579| 10.001935| 12.870415| 18.130588|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 2.4751e+01| 7.574726| 10.232539| 9.918625| 13.184939| 19.214114|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 2.3796e+01| 7.407586| 10.023690| 9.657584| 12.995239| 10.822917|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 2.3047e+01| 7.392159| 10.194699| 9.921822| 13.104957| 7.714529|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 7.39216| < -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 10 non-physical points in the solution.
Warning: 234 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 = -36.250707 Cd = -4.699017
--> Cmx = -0.638902 Cmy = 6.00351 Cmz = -0.388151
--> Cx = -4.06564 Cy = -0.352021 Cz = -36.327195
real 9m42.129s
user 7m3.347s
sys 1m6.104s
+ 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 /Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64/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 0m57.783s
user 0m58.516s
sys 0m36.781s
+ 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 /Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64/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 = 831
Number of elements = 962
Number of triangle elements = 0
Number of quadrilateral elements = 962
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 = 832
Total number of elements = 962
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 = 831
Number of elements = 962
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 962
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 = 832
Combined Number of elements = 963
Combined Elemental Nodes = 1
Combined Elemental Rods = 0
Combined Elemental Tria3 = 0
Combined Elemental Quad4 = 962
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 832)
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 : 1.93141e-08
2 : 0.0014201
3 : 0.00174471
4 : 0.00323704
5 : 0.00324327
6 : 0.00432932
7 : 0.00512433
8 : 0.00873482
9 : 0.0100619
10: 0.0107025
real 3m11.570s
user 2m54.920s
sys 1m26.789s
+ 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 /Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64/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...
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
==> Running mASTROS post-analysis...
--> Maximum displacements:
--> Tmax 238433.3403112283
--> T1max 16861.9
--> T2max 16414.9
--> T3max 237286.0
real 0m23.495s
user 0m38.012s
sys 0m25.194s
+ 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 /Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64/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...
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
==> Running mASTROS post-analysis...
--> Maximum displacements:
--> Tmax 52594.60117638786
--> T1max 4359.68
--> T2max 3216.5
--> T3max 52322.2
real 0m21.377s
user 0m37.034s
sys 0m24.994s
+ status=0
+ set +x
=================================================
data/session09/4_astros_Composite.py passed (as expected)
=================================================
[macys.mit.edu:56610] shmem: mmap: an error occurred while determining whether or not /var/folders/xs/_fh4l1p54zqcl6mbk4zclcfr0000gp/T//ompi.macys.502/jf.0/2220818432/sm_segment.macys.502.845f0000.0 could be created.
=================================================
6_tacs_StaticCantilever.py test;
+ python 6_tacs_StaticCantilever.py
+ tee -a /Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64/CAPS/training/2023/training.log
[macys.mit.edu:56625] shmem: mmap: an error occurred while determining whether or not /var/folders/xs/_fh4l1p54zqcl6mbk4zclcfr0000gp/T//ompi.macys.502/jf.0/2020933632/sm_segment.macys.502.78750000.0 could be created.
==> 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 = 511406.70938906947
functional ks_vmfailure = 0.019135051727271438
real 0m22.932s
user 0m35.509s
sys 0m15.852s
+ 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 /Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64/CAPS/training/2023/training.log
[macys.mit.edu:56673] shmem: mmap: an error occurred while determining whether or not /var/folders/xs/_fh4l1p54zqcl6mbk4zclcfr0000gp/T//ompi.macys.502/jf.0/1600782336/sm_segment.macys.502.5f6a0000.0 could be created.
==> 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: 5.76, nnz(ILU) = 206656
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
/Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64/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 [351348.8584378]
--> ks_vmfailure [0.18465374]
--> mass [351348.8584378]
--> ks_vmfailure [0.18465374]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00701607]]
--> ks_vmfailure skinThk [[-0.77735769]]
--> ks_vmfailure sparThk [[-0.00419852]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.001]
--> skinThk [0.00739074]
--> sparThk [0.001]
--> mass [164778.06753421]
--> ks_vmfailure [0.18458271]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.27193778]]
--> ks_vmfailure skinThk [[-0.30939956]]
--> ks_vmfailure sparThk [[-0.20978605]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.001]
--> skinThk [0.001]
--> sparThk [0.02273644]
--> mass [129232.41385728]
--> ks_vmfailure [0.20239501]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.001]
--> skinThk [0.00647627]
--> sparThk [0.00411034]
--> mass [159691.72878047]
--> ks_vmfailure [0.18468723]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.28428467]]
--> ks_vmfailure skinThk [[-0.36623707]]
--> ks_vmfailure sparThk [[-0.04561164]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.01797054]
--> skinThk [0.001]
--> sparThk [0.0012247]
--> mass [135761.31599909]
--> ks_vmfailure [0.20097431]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00336292]
--> skinThk [0.00571377]
--> sparThk [0.00370855]
--> mass [156359.73995058]
--> ks_vmfailure [0.18476613]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.04724024]]
--> ks_vmfailure skinThk [[-0.42968567]]
--> ks_vmfailure sparThk [[-0.05558717]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00375419]
--> skinThk [0.0118629]
--> sparThk [0.00560564]
--> mass [221348.46889819]
--> ks_vmfailure [0.18335024]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00340205]
--> skinThk [0.00632869]
--> sparThk [0.00389826]
--> mass [162858.61284534]
--> ks_vmfailure [0.18451389]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.0033671]
--> skinThk [0.00577947]
--> sparThk [0.00372882]
--> mass [157054.09556222]
--> ks_vmfailure [0.18473688]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.04660765]]
--> ks_vmfailure skinThk [[-0.42085611]]
--> ks_vmfailure sparThk [[-0.05458697]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.001]
--> skinThk [0.0114244]
--> sparThk [0.01236645]
--> mass [220187.17438764]
--> ks_vmfailure [0.18349008]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.22376308]]
--> ks_vmfailure skinThk [[-0.11542908]]
--> ks_vmfailure sparThk [[-0.00924893]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00726772]
--> skinThk [0.01192034]
--> sparThk [0.01564752]
--> mass [242329.88574404]
--> ks_vmfailure [0.18318718]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00374643]
--> skinThk [0.01164171]
--> sparThk [0.01380417]
--> mass [229889.80169957]
--> ks_vmfailure [0.18327675]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.0024241]
--> skinThk [0.01153708]
--> sparThk [0.01311195]
--> mass [225218.2736428]
--> ks_vmfailure [0.18333401]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.04342337]]
--> ks_vmfailure skinThk [[-0.10932276]]
--> ks_vmfailure sparThk [[-0.00862543]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00273423]
--> skinThk [0.02300858]
--> sparThk [0.0208162]
--> mass [351071.64335651]
--> ks_vmfailure [0.18265072]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00246133]
--> skinThk [0.01291395]
--> sparThk [0.01403666]
--> mass [240323.86796358]
--> ks_vmfailure [0.18319035]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.00615236]
--> skinThk [0.02577931]
--> sparThk [0.00214916]
--> mass [361343.31744605]
--> ks_vmfailure [0.18263733]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00640621]]
--> ks_vmfailure skinThk [[-0.02501965]]
--> ks_vmfailure sparThk [[-0.04131297]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00713229]
--> skinThk [0.02677305]
--> sparThk [0.0168223]
--> mass [392609.86291328]
--> ks_vmfailure [0.18251681]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00663017]
--> skinThk [0.02626385]
--> sparThk [0.00930372]
--> mass [376588.76116566]
--> ks_vmfailure [0.18255199]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.0064128]
--> skinThk [0.02604342]
--> sparThk [0.00604892]
--> mass [369653.21087943]
--> ks_vmfailure [0.18257185]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00605012]]
--> ks_vmfailure skinThk [[-0.02434576]]
--> ks_vmfailure sparThk [[-0.00555063]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.0097372]
--> skinThk [0.04835412]
--> sparThk [0.00759194]
--> mass [602336.93932585]
--> ks_vmfailure [0.18225672]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.00752075]
--> skinThk [0.03347906]
--> sparThk [0.00656318]
--> mass [447201.32423534]
--> ks_vmfailure [0.18242234]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00423673]]
--> ks_vmfailure skinThk [[-0.01486475]]
--> ks_vmfailure sparThk [[-0.00451743]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.01240423]
--> skinThk [0.05849094]
--> sparThk [0.01317201]
--> mass [716841.47781672]
--> ks_vmfailure [0.18217976]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00154606]]
--> ks_vmfailure skinThk [[-0.00498155]]
--> ks_vmfailure sparThk [[-0.00115575]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.01929414]
--> skinThk [0.09078555]
--> sparThk [0.02029672]
--> mass [1064340.58921378]
--> ks_vmfailure [0.18206339]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00064649]]
--> ks_vmfailure skinThk [[-0.00208485]]
--> ks_vmfailure sparThk [[-0.00048511]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.02545586]
--> skinThk [0.11766696]
--> sparThk [0.02722908]
--> mass [1355784.09501524]
--> ks_vmfailure [0.18201458]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.02816247]
--> skinThk [0.1278486]
--> sparThk [0.03061507]
--> mass [1467935.54338862]
--> ks_vmfailure [0.1820012]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.02874638]
--> skinThk [0.12860072]
--> sparThk [0.03166063]
--> mass [1478053.22646291]
--> ks_vmfailure [0.18200001]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.02995584]
--> skinThk [0.12773274]
--> sparThk [0.03432163]
--> mass [1475323.18211848]
--> ks_vmfailure [0.18200005]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00028252]]
--> ks_vmfailure skinThk [[-0.00104812]]
--> ks_vmfailure sparThk [[-0.000184]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.03300207]
--> skinThk [0.12582909]
--> sparThk [0.0407494]
--> mass [1470920.60962544]
--> ks_vmfailure [0.18200021]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03417052]
--> skinThk [0.12543856]
--> sparThk [0.04303502]
--> mass [1472403.19847778]
--> ks_vmfailure [0.18200002]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03466537]
--> skinThk [0.12523006]
--> sparThk [0.04393562]
--> mass [1472509.9882878]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03477343]
--> skinThk [0.12519386]
--> sparThk [0.04405893]
--> mass [1472530.53633059]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03499382]
--> skinThk [0.12513457]
--> sparThk [0.04415997]
--> mass [1472520.48038099]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03528602]
--> skinThk [0.12508833]
--> sparThk [0.04404571]
--> mass [1472505.62701918]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03554752]
--> skinThk [0.12509498]
--> sparThk [0.04357429]
--> mass [1472488.99260686]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03557543]
--> skinThk [0.12515336]
--> sparThk [0.04308252]
--> mass [1472485.57497966]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03549811]
--> skinThk [0.12518987]
--> sparThk [0.04292621]
--> mass [1472487.81481868]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03546495]
--> skinThk [0.12519741]
--> sparThk [0.04292079]
--> mass [1472488.37514104]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> 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: 5.76, nnz(ILU) = 206656
--> ribThk [0.03546229]
--> skinThk [0.12519748]
--> sparThk [0.04292444]
--> mass [1472488.42506508]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00022004]]
--> ks_vmfailure skinThk [[-0.00107641]]
--> ks_vmfailure sparThk [[-0.00014103]]
[0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656
--> ribThk [0.03546228]
--> skinThk [0.12519745]
--> sparThk [0.0429247]
--> mass [1472488.42560328]
--> ks_vmfailure [0.182]
--> mass ribThk [[2050883.76812598]]
--> mass skinThk [[10032748.6549307]]
--> mass sparThk [[1314431.32692686]]
--> ks_vmfailure ribThk [[-0.00022004]]
--> ks_vmfailure skinThk [[-0.00107641]]
--> ks_vmfailure sparThk [[-0.00014103]]
Optimization terminated successfully (Exit mode 0)
Current function value: 4.2071097874379575
Iterations: 29
Function evaluations: 39
Gradient evaluations: 29
Optimization Complete
-----------------------------------
==> Optimized value:
--> ribThk [0.03546228]
--> skinThk [0.12519745]
--> sparThk [0.0429247]
real 1m20.313s
user 1m33.493s
sys 0m15.832s
+ 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 /Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64/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 Darwin 23.4.0 x86_64
AFLR2 : Compile Date 06/11/24 @ 06:29PM
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 Darwin 23.5.0 x86_64
AFLR4 : Compile Date 07/19/24 @ 07:21PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.26
EGADS : OpenCASCADE Version 7.7.0
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 = 0.232 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 Darwin 23.4.0 x86_64
AFLR2 : Compile Date 06/11/24 @ 06:29PM
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 Darwin 23.5.0 x86_64
AFLR4 : Compile Date 07/19/24 @ 07:21PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.26
EGADS : OpenCASCADE Version 7.7.0
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 Darwin 22.6.0 x86_64
AFLR3 : Compile Date 11/01/23 @ 12:19PM
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 = 0.022 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 95707
AFLR3 IG : Nodes, Elements = 11570 95485
AFLR3 IG : Nodes, Elements = 11563 61784
AFLR3 IG : Nodes, Elements = 11563 61867
AFLR3 IG : Nodes, Elements = 11563 39399
AFLR3 IG : Nodes, Elements = 11563 34612
AFLR3 : CPU Time = 0.347 seconds
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
AFLR3 GG : Nodes, Elements = 11563 34612
AFLR3 GG : Nodes, Elements = 16472 49618
AFLR3 GG : Nodes, Elements = 16472 70280
AFLR3 GG : Nodes, Elements = 16472 65236
AFLR3 GG : Nodes, Elements = 20364 77588
AFLR3 GG : Nodes, Elements = 20364 91643
AFLR3 GG : Nodes, Elements = 20364 86746
AFLR3 GG : Nodes, Elements = 24767 100584
AFLR3 GG : Nodes, Elements = 24767 117584
AFLR3 GG : Nodes, Elements = 24767 112454
AFLR3 GG : Nodes, Elements = 29427 126756
AFLR3 GG : Nodes, Elements = 29427 145198
AFLR3 GG : Nodes, Elements = 29427 140108
AFLR3 GG : Nodes, Elements = 34209 154758
AFLR3 GG : Nodes, Elements = 34209 173466
AFLR3 GG : Nodes, Elements = 34209 168382
AFLR3 GG : Nodes, Elements = 38993 182937
AFLR3 GG : Nodes, Elements = 38993 201717
AFLR3 GG : Nodes, Elements = 38993 196657
AFLR3 GG : Nodes, Elements = 43732 211082
AFLR3 GG : Nodes, Elements = 43732 229850
AFLR3 GG : Nodes, Elements = 43732 224810
AFLR3 GG : Nodes, Elements = 48505 239274
AFLR3 GG : Nodes, Elements = 48505 257981
AFLR3 GG : Nodes, Elements = 48505 253045
AFLR3 GG : Nodes, Elements = 53249 267410
AFLR3 GG : Nodes, Elements = 53249 286138
AFLR3 GG : Nodes, Elements = 53249 281223
AFLR3 GG : Nodes, Elements = 57861 295184
AFLR3 GG : Nodes, Elements = 57861 313265
AFLR3 GG : Nodes, Elements = 57861 308586
AFLR3 GG : Nodes, Elements = 62381 322238
AFLR3 GG : Nodes, Elements = 62381 339802
AFLR3 GG : Nodes, Elements = 62381 335387
AFLR3 GG : Nodes, Elements = 66720 348477
AFLR3 GG : Nodes, Elements = 66720 365554
AFLR3 GG : Nodes, Elements = 66720 361116
AFLR3 GG : Nodes, Elements = 70966 373931
AFLR3 GG : Nodes, Elements = 70966 390737
AFLR3 GG : Nodes, Elements = 70966 386334
AFLR3 GG : Nodes, Elements = 75014 398537
AFLR3 GG : Nodes, Elements = 75014 414352
AFLR3 GG : Nodes, Elements = 75014 410363
AFLR3 GG : Nodes, Elements = 79017 422429
AFLR3 GG : Nodes, Elements = 79017 438094
AFLR3 GG : Nodes, Elements = 79017 434113
AFLR3 GG : Nodes, Elements = 82887 445792
AFLR3 GG : Nodes, Elements = 82887 460854
AFLR3 GG : Nodes, Elements = 82887 457090
AFLR3 GG : Nodes, Elements = 86555 468139
AFLR3 GG : Nodes, Elements = 86555 482529
AFLR3 GG : Nodes, Elements = 86555 478908
AFLR3 GG : Nodes, Elements = 90128 489665
AFLR3 GG : Nodes, Elements = 90128 503581
AFLR3 GG : Nodes, Elements = 90128 500079
AFLR3 GG : Nodes, Elements = 93630 510618
AFLR3 GG : Nodes, Elements = 93630 524254
AFLR3 GG : Nodes, Elements = 93630 520783
AFLR3 GG : Nodes, Elements = 96934 530726
AFLR3 GG : Nodes, Elements = 96934 543663
AFLR3 GG : Nodes, Elements = 96934 540473
AFLR3 GG : Nodes, Elements = 100101 549998
AFLR3 GG : Nodes, Elements = 100101 562396
AFLR3 GG : Nodes, Elements = 100101 559255
AFLR3 GG : Nodes, Elements = 103103 568274
AFLR3 GG : Nodes, Elements = 103103 580164
AFLR3 GG : Nodes, Elements = 103103 577101
AFLR3 GG : Nodes, Elements = 105949 585661
AFLR3 GG : Nodes, Elements = 105949 596814
AFLR3 GG : Nodes, Elements = 105949 594056
AFLR3 GG : Nodes, Elements = 108655 602189
AFLR3 GG : Nodes, Elements = 108655 612848
AFLR3 GG : Nodes, Elements = 108655 610196
AFLR3 GG : Nodes, Elements = 111113 617579
AFLR3 GG : Nodes, Elements = 111113 627252
AFLR3 GG : Nodes, Elements = 111113 624771
AFLR3 GG : Nodes, Elements = 113487 631900
AFLR3 GG : Nodes, Elements = 113487 641112
AFLR3 GG : Nodes, Elements = 113487 638912
AFLR3 GG : Nodes, Elements = 115603 645269
AFLR3 GG : Nodes, Elements = 115603 653470
AFLR3 GG : Nodes, Elements = 115603 651412
AFLR3 GG : Nodes, Elements = 117563 657296
AFLR3 GG : Nodes, Elements = 117563 664969
AFLR3 GG : Nodes, Elements = 117563 663084
AFLR3 GG : Nodes, Elements = 119267 668199
AFLR3 GG : Nodes, Elements = 119267 674790
AFLR3 GG : Nodes, Elements = 119267 673192
AFLR3 GG : Nodes, Elements = 120731 677586
AFLR3 GG : Nodes, Elements = 120731 683561
AFLR3 GG : Nodes, Elements = 120731 681933
AFLR3 GG : Nodes, Elements = 121879 685379
AFLR3 GG : Nodes, Elements = 121879 689935
AFLR3 GG : Nodes, Elements = 121879 688766
AFLR3 GG : Nodes, Elements = 122786 691489
AFLR3 GG : Nodes, Elements = 122786 695172
AFLR3 GG : Nodes, Elements = 122786 694163
AFLR3 GG : Nodes, Elements = 123402 696011
AFLR3 GG : Nodes, Elements = 123402 698518
AFLR3 GG : Nodes, Elements = 123402 697802
AFLR3 GG : Nodes, Elements = 123794 698979
AFLR3 GG : Nodes, Elements = 123794 700568
AFLR3 GG : Nodes, Elements = 123794 700108
AFLR3 GG : Nodes, Elements = 124011 700760
AFLR3 GG : Nodes, Elements = 124011 701717
AFLR3 GG : Nodes, Elements = 124011 701383
AFLR3 GG : Nodes, Elements = 124107 701671
AFLR3 GG : Nodes, Elements = 124107 702071
AFLR3 GG : Nodes, Elements = 124107 701935
AFLR3 GG : Nodes, Elements = 124140 702034
AFLR3 GG : Nodes, Elements = 124140 702164
AFLR3 GG : Nodes, Elements = 124140 702120
AFLR3 GG : Nodes, Elements = 124151 702153
AFLR3 GG : Nodes, Elements = 124151 702196
AFLR3 GG : Nodes, Elements = 124151 702183
AFLR3 GG : Nodes, Elements = 124152 702186
AFLR3 GG : Nodes, Elements = 124152 702189
AFLR3 GG : Nodes, Elements = 124152 702187
AFLR3 GG : Nodes, Elements = 124167 702232
AFLR3 GG : Nodes, Elements = 124167 702280
AFLR3 GG : Nodes, Elements = 124167 702266
AFLR3 GG : Nodes, Elements = 124178 702299
AFLR3 GG : Nodes, Elements = 124178 702345
AFLR3 GG : Nodes, Elements = 124178 702332
AFLR3 GG : Nodes, Elements = 124179 702335
AFLR3 GG : Nodes, Elements = 124179 702340
AFLR3 GG : Nodes, Elements = 124179 702338
AFLR3 : CPU Time = 5.513 seconds
AFLR3 QI : QUALITY IMPROVEMENT
AFLR3 QI : Nodes, Elements = 124179 702338
AFLR3 QI : Nodes, Elements = 123493 698500
AFLR3 QI : Nodes, Elements = 123429 698136
AFLR3 QI : Nodes, Elements = 123424 698106
AFLR3 QI : Nodes, Elements = 123422 698098
AFLR3 QI : Nodes, Elements = 123422 701271
AFLR3 QI : Nodes, Elements = 123422 697785
AFLR3 QI : Nodes, Elements = 123422 696258
AFLR3 QI : Nodes, Elements = 123422 696656
AFLR3 QI : Nodes, Elements = 123422 696019
AFLR3 QI : Nodes, Elements = 123422 695859
AFLR3 QI : Nodes, Elements = 123422 696243
AFLR3 QI : Nodes, Elements = 123422 695879
AFLR3 QI : Nodes, Elements = 123422 695807
AFLR3 QI : Nodes, Elements = 123422 696148
AFLR3 QI : Nodes, Elements = 123422 695834
AFLR3 QI : Nodes, Elements = 123422 695788
AFLR3 QI : Nodes, Elements = 123422 696191
AFLR3 QI : Nodes, Elements = 123422 695804
AFLR3 QI : Nodes, Elements = 123422 695770
AFLR3 QI : Nodes, Elements = 123423 695774
AFLR3 QI : Nodes, Elements = 123423 696110
AFLR3 QI : Nodes, Elements = 123423 695779
AFLR3 QI : Nodes, Elements = 123423 695769
AFLR3 QI : Nodes, Elements = 123423 696180
AFLR3 QI : Nodes, Elements = 123423 695801
AFLR3 QI : Nodes, Elements = 123423 695764
AFLR3 : CPU Time = 2.033 seconds
AFLR3 : DONE
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 695764
UG3 : Min, Max Ang = 8.413 163.9
UG3 : Average Angle = 70.2
UG3 : No. Angle>160.0 = 3
UG3 : No. Angle>179.9 = 0
UG3 : VOL CHECK
UG3 : Total-Volume = 5.96e+10
UG3 : No. Tet Elems = 695764
UG3 : Min Vol = 0.00105
UG3 : Average Vol = 8.57e+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 = 695764
UG3 : Min, Max Q = 0.0946 1
UG3 : Average Q = 0.902
UG3 : No. Q< 0.1 = 2
UG3 : No. Q< 0.01 = 0
OVERALL : CPU Time = 8.075 seconds
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 695764
UG3 : Min, Max Ang = 8.413 163.9
UG3 : Average Angle = 70.2
UG3 : No. Angle>160.0 = 3
UG3 : No. Angle>179.9 = 0
UG3 : VOL CHECK
UG3 : Total-Volume = 5.96e+10
UG3 : No. Tet Elems = 695764
UG3 : Min Vol = 0.00105
UG3 : Average Vol = 8.57e+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 = 695764
UG3 : Min, Max Q = 0.272 1
UG3 : Average Q = 0.86
UG3 : No. Q< 0.1 = 0
UG3 : No. Q< 0.01 = 0
UG3 : CPU Time = 0.000 seconds
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.26
EGADS : OpenCASCADE Version 7.7.0
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 = 123423
Number of elements = 718882
Number of triangles = 23118
Number of quadrilatarals = 0
Number of tetrahedrals = 695764
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.
123423 grid points.
695764 volume elements.
2 surface markers.
23082 boundary elements in index 0 (Marker = BC_1).
36 boundary elements in index 1 (Marker = BC_2).
695764 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: 1.54048. Standard deviation K: 3.02418.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 41.0577| 86.8574|
| CV Face Area Aspect Ratio| 1.05911| 2152.01|
| CV Sub-Volume Ratio| 1.03138| 42924.4|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 123423| 1/1.00| 10|
| 1| 20328| 1/6.07| 8.22225|
| 2| 3065| 1/6.63| 6.56438|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 97.6729 m.
Wetted area = 8661.74 m^2.
Area projection in the x-plane = 677.811 m^2, y-plane = 441.377 m^2, z-plane = 4150.71 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| 2.8503e+00| 0.772952| 2.931963| 2.669215| 6.242058| -0.773113|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.6336e+00| 3.376000| 5.785394| 5.588853| 8.837860| -0.601775|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.5599e+00| 5.131790| 7.572654| 7.362761| 10.600167| -12.601225|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 2.4827e+00| 6.778730| 9.344080| 9.034119| 12.202965| 6.224829|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.4509e+00| 7.140059| 9.524868| 9.487698| 12.483259| 0.646754|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 7.14006| < -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 297 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 = 3.925224e+12, tgt = 3.925224e+12, diff = 1.580339e+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 = 3.688348e+12, tgt = 3.688348e+12, diff = 5.044775e+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 = 1.615502e+09, tgt = 1.615502e+09, diff = 8.270512e+00
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 = 1.280540e+09, tgt = 1.280541e+09, diff = 1.321491e+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......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
==> 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.
123423 grid points.
695764 volume elements.
2 surface markers.
23082 boundary elements in index 0 (Marker = BC_1).
36 boundary elements in index 1 (Marker = BC_2).
695764 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 31.741884 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.
123423 grid points.
695764 volume elements.
2 surface markers.
23082 boundary elements in index 0 (Marker = BC_1).
36 boundary elements in index 1 (Marker = BC_2).
695764 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 333760 TETRAHEDRON volume elements.
There has been a re-orientation of 7096 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 5.98634e+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: 64.3438. Mean K: 1.52452. Standard deviation K: 2.67858.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 0.343889| 81.0669|
| CV Face Area Aspect Ratio| 1.4096| 59685.8|
| CV Sub-Volume Ratio| 1.10541| 5.52539e+06|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 123423| 1/1.00| 10|
| 1| 20308| 1/6.08| 8.21955|
| 2| 3115| 1/6.52| 6.59989|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 156.502 m.
Wetted area = 3.77463e+06 m^2.
Area projection in the x-plane = 1.60138e+06 m^2, y-plane = 477626 m^2, z-plane = 123894 m^2.
Max. coordinate in the x-direction = 194.871 m, y-direction = 156.502 m, z-direction = 651.431 m.
Min. coordinate in the x-direction = 40.783 m, y-direction = -130.607 m, z-direction = -898.471 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| 2.9383e+00| 5.115204| 8.082540| 7.892719| 10.584310| 0.023989|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.0218e+00| 5.716121| 8.211975| 8.043489| 11.173867| 0.036085|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.0418e+00| 6.417447| 8.946327| 8.614955| 11.898134| 0.069982|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.0583e+00| 6.243553| 8.753624| 8.496941| 11.719074| 0.080785|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.0704e+00| 6.475979| 9.005316| 8.775785| 11.980360| 0.108597|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 6.47598| < -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 6532 non-physical points in the solution.
Warning: 2621 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 = 1.590139e+12, tgt = 1.590139e+12, diff = 2.987891e+01
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 = 1.565754e+12, tgt = 1.565754e+12, diff = 1.740991e+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 = 5.120748e+08, tgt = 5.120749e+08, diff = 1.003084e+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 = 3.472515e+08, tgt = 3.472517e+08, diff = 1.360779e+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......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
==> Running ASTROS post-analysis...
real 2m12.917s
user 2m22.606s
sys 0m22.690s
+ 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 [macys] is in [[windows10x64]]
Run condition [Execution node ] preventing perform for step [Execute Windows batch command]
[GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64')
[Clang] Skipping post processing
[Clang] No filter has been set, publishing all 0 issues
[Clang] Repository miner is not configured, skipping repository mining
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64')
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCapsQuick/7.7/CAPS/training/DARWIN64')
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] No valid reference build found
[Static Analysis] All reported issues will be considered outstanding
[Static Analysis] No quality gates have been set - skipping
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_RegCapsQuick/CASREV=7.7,ESP_ARCH=DARWIN64,buildnode=macys #47'.
[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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