+-----------------------------------------------------------------------+
--------------------------- 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 Force - Pressure + Viscous
Cl = 0.072253 Cd = -0.01151
Cmz = 0.070975
Cx = -0.01151 Cy = 0.072253
Pressure Contribution
Cl_p = 0.072253 Cd_p = -0.01151
Cmz_p = 0.070975
Cx_p = -0.01151 Cy_p = 0.072253
Viscous Contribution
Cl_v = 0.0 Cd_v = 0.0
Cmz_v = 0.0
Cx_v = 0.0 Cy_v = 0.0
real 0m2.863s
user 0m2.845s
sys 0m0.507s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_and_AFLR2_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'su2_and_AFLR4_AFLR3_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
su2_and_AFLR4_AFLR3_PyTest.py test;
+ python -u su2_and_AFLR4_AFLR3_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
AFLR4 : Proximity BG Surface Grid Generation Skipped
AFLR4 : No Modifications Required
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value
Writing TECPLOT file: AFLR4_Mesh.dat ....
Finished writing TECPLOT file
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
Getting volume mesh
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.7
AFLR2 : Version Date 07/16/23 @ 01:42PM
AFLR2 : Compile OS Darwin 22.6.0 arm64
AFLR2 : Compile Date 08/01/23 @ 11:39PM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR4 : ---------------------------------------
AFLR4 : AFLR4 LIBRARY
AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4 : Version Number 11.5.9
AFLR4 : Version Date 08/14/23 @ 12:27AM
AFLR4 : Compile OS Darwin 22.6.0 arm64
AFLR4 : Compile Date 08/14/23 @ 12:31AM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.7.0
EGADS : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.7.0
EGADS : ---------------------------------------
Volume mesh:
Number of nodes = 38502
Number of elements = 221920
Number of triangles = 12446
Number of quadrilatarals = 0
Number of tetrahedrals = 209474
Number of pyramids = 0
Number of prisms = 0
Number of hexahedrals = 0
Writing TECPLOT file: AFLR3_Mesh.dat ....
Finished writing TECPLOT file
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wake
Boundary condition name - Wing1
Boundary condition name - Wing2
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Harrier (8.0.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.5901.
Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 50 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 15.8114 m.
Surface(s) where the force coefficients are evaluated and
their reference origin for moment computation:
- BC_1 (0, 0, 0).
- BC_2 (0, 0, 0) m.
Surface(s) plotted in the output file: BC_1, BC_2.
Input mesh file name: ../aflr3/aflr3_0.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 10.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-8.
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|
| PARAVIEW| 250|
| SURFACE_PARAVIEW| 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_su2AFLRTest.dat.
Surface file name: surface_flow_su2AFLRTest.
Volume file name: flow_su2AFLRTest.
Restart file name: restart_flow_su2AFLRTest.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
| | BC_2|
+-----------------------------------------------------------------------+
| Far-field| BC_4|
+-----------------------------------------------------------------------+
| Internal boundary| BC_3|
+-----------------------------------------------------------------------+
-------------------- 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.
38502 grid points.
209474 volume elements.
4 surface markers.
6594 boundary elements in index 0 (Marker = BC_1).
5358 boundary elements in index 1 (Marker = BC_2).
74 boundary elements in index 2 (Marker = BC_3).
420 boundary elements in index 3 (Marker = BC_4).
209474 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: 2.08667e+06.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 4873.1. Mean K: 61.8683. Standard deviation K: 266.942.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 25.7373| 86.6783|
| CV Face Area Aspect Ratio| 1.09466| 7304.38|
| CV Sub-Volume Ratio| 1.04044| 69268.7|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 38502| 1/1.00| 10|
| 1| 6385| 1/6.03| 8.24107|
| 2| 1003| 1/6.37| 6.66994|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.90569 m.
Wetted area = 118.038 m^2.
Area projection in the x-plane = 11.1422 m^2, y-plane = 4.96709 m^2, z-plane = 55.4183 m^2.
Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.582636 m.
Min. coordinate in the x-direction = 0 m, y-direction = -7.90569 m, z-direction = -0.41192 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Boundary marker BC_2 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 226952| 1| m^2/s^2| 226952|
| Velocity-X| 200.779| 1| m/s| 200.779|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 3.50461| 1| m/s| 3.50461|
| Velocity Magnitude| 200.809| 1| m/s| 200.809|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.5901|
+------------------------------------------------------------------------------+
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| 7.7108e-01| -0.060087| 2.302216| 2.037805| 5.430808| 1.979346|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 7.5904e-01| -0.010036| 2.482646| 2.186974| 5.492648| 2.690164|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 7.5292e-01| 0.015122| 2.560028| 2.424390| 5.513110| 4.144990|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 7.6448e-01| -0.037042| 2.579202| 2.559777| 5.446956| 6.076344|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 7.6151e-01| -0.081173| 2.578114| 2.616175| 5.391591| 7.699778|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 7.6219e-01| -0.085972| 2.582416| 2.631873| 5.398797| 8.892926|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 7.6267e-01| -0.096180| 2.574091| 2.638010| 5.401796| 9.787209|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 7.5849e-01| -0.128924| 2.539338| 2.641609| 5.371412| 10.317352|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 7.5650e-01| -0.184841| 2.469269| 2.632268| 5.306572| 10.430833|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 7.5555e-01| -0.254301| 2.406660| 2.598073| 5.225779| 10.218562|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.254301| < -8| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_su2AFLRTest.dat |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|CSV file |surface_flow_su2AFLRTest.csv |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview |flow_su2AFLRTest.vtu |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview surface |surface_flow_su2AFLRTest.vtu |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.799154 Cd = 0.078206
Cmx = 0.000491 Cmy = -0.204969 Cmz = 0.000591
Cx = 0.064247 Cy = 0.000689 Cz = 0.800398
Pressure Contribution
Cl_p = 0.799154 Cd_p = 0.078206
Cmx_p = 0.000491 Cmy_p = -0.204969 Cmz_p = 0.000591
Cx_p = 0.064247 Cy_p = 0.000689 Cz_p = 0.800398
Viscous Contribution
Cl_v = 0.0 Cd_v = 0.0
Cmx_v = 0.0 Cmy_v = 0.0 Cmz_v = 0.0
Cx_v = 0.0 Cy_v = 0.0 Cz_v = 0.0
real 0m24.447s
user 0m22.703s
sys 0m0.533s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_and_AFLR4_AFLR3_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'su2_Morph_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
su2_Morph_PyTest.py test;
+ python -u su2_Morph_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
AFLR4 : Proximity BG Surface Grid Generation Skipped
AFLR4 : No Modifications Required
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value
Writing TECPLOT file: pyCAPS_AFLR4_AFLR3.dat ....
Finished writing TECPLOT file
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
Getting volume mesh
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.7
AFLR2 : Version Date 07/16/23 @ 01:42PM
AFLR2 : Compile OS Darwin 22.6.0 arm64
AFLR2 : Compile Date 08/01/23 @ 11:39PM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR4 : ---------------------------------------
AFLR4 : AFLR4 LIBRARY
AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4 : Version Number 11.5.9
AFLR4 : Version Date 08/14/23 @ 12:27AM
AFLR4 : Compile OS Darwin 22.6.0 arm64
AFLR4 : Compile Date 08/14/23 @ 12:31AM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.7.0
EGADS : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.7.0
EGADS : ---------------------------------------
Volume mesh:
Number of nodes = 55692
Number of elements = 322597
Number of triangles = 15872
Number of quadrilatarals = 0
Number of tetrahedrals = 306725
Number of pyramids = 0
Number of prisms = 0
Number of hexahedrals = 0
Writing TECPLOT file: pyCAPS_AFLR4_AFLR3_VolMesh.dat ....
Finished writing TECPLOT file
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wake
Boundary condition name - Wing1
Boundary condition name - Wing2
Done getting CFD boundary conditions
Writing SU2 surface file
Writing SU2 Motion File - su2AFLRTest_motion.dat
Writing boundary flags
- bcProps.surfaceProp[0].surfaceType = 3
- bcProps.surfaceProp[1].surfaceType = 15
- bcProps.surfaceProp[2].surfaceType = 1
- bcProps.surfaceProp[3].surfaceType = 1
Done boundary flags
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Harrier (8.0.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.5901.
Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 40 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 14.1421 m.
Surface(s) where the force coefficients are evaluated and
their reference origin for moment computation:
- BC_1 (0, 0, 0).
- BC_2 (0, 0, 0) m.
Surface(s) plotted in the output file: BC_1, BC_2.
Surface(s) affected by the design variables: BC_1, BC_2.
Input mesh file name: ../volumeMesh/aflr3_0.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 10.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-8.
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|
| PARAVIEW| 250|
| SURFACE_PARAVIEW| 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_su2AFLRTest.dat.
Surface file name: surface_flow_su2AFLRTest.
Volume file name: flow_su2AFLRTest.
Restart file name: restart_flow_su2AFLRTest.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
| | BC_2|
+-----------------------------------------------------------------------+
| Far-field| BC_4|
+-----------------------------------------------------------------------+
| Internal boundary| BC_3|
+-----------------------------------------------------------------------+
-------------------- 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.
55692 grid points.
306725 volume elements.
4 surface markers.
9958 boundary elements in index 0 (Marker = BC_1).
5414 boundary elements in index 1 (Marker = BC_2).
80 boundary elements in index 2 (Marker = BC_3).
420 boundary elements in index 3 (Marker = BC_4).
306725 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: 2.08667e+06.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 5523.74. Mean K: 58.8178. Standard deviation K: 282.533.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 17.6334| 85.6893|
| CV Face Area Aspect Ratio| 1.03551| 10026.2|
| CV Sub-Volume Ratio| 1.03837| 55476.6|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 55692| 1/1.00| 10|
| 1| 9209| 1/6.05| 8.23312|
| 2| 1415| 1/6.51| 6.6146|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.07107 m.
Wetted area = 96.2324 m^2.
Area projection in the x-plane = 7.65774 m^2, y-plane = 4.21853 m^2, z-plane = 45.5887 m^2.
Max. coordinate in the x-direction = 12.3872 m, y-direction = 7.07107 m, z-direction = 0.521791 m.
Min. coordinate in the x-direction = 0 m, y-direction = -7.07107 m, z-direction = -0.0650201 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Boundary marker BC_2 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 226952| 1| m^2/s^2| 226952|
| Velocity-X| 200.779| 1| m/s| 200.779|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 3.50461| 1| m/s| 3.50461|
| Velocity Magnitude| 200.809| 1| m/s| 200.809|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.5901|
+------------------------------------------------------------------------------+
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| 1.1028e+00| -0.456432| 1.874717| 1.658147| 5.034463| 0.751359|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.1138e+00| -0.486415| 2.011739| 1.708650| 5.010503| 1.410135|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.0981e+00| -0.426910| 2.085510| 1.930071| 5.059947| 3.183469|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.0853e+00| -0.413221| 2.123390| 2.080595| 5.061524| 6.846574|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.1016e+00| -0.415069| 2.144313| 2.168724| 5.045574| 12.481741|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.0827e+00| -0.408728| 2.161839| 2.210835| 5.050178| 19.569122|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.0824e+00| -0.400272| 2.162405| 2.231094| 5.064509| 27.279075|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.0893e+00| -0.415420| 2.140420| 2.247896| 5.053374| 31.968213|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.1006e+00| -0.459344| 2.092599| 2.258672| 5.008518| 30.523517|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.1044e+00| -0.475584| 2.031862| 2.254220| 4.985969| 25.858195|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.475584| < -8| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_su2AFLRTest.dat |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|CSV file |surface_flow_su2AFLRTest.csv |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview |flow_su2AFLRTest.vtu |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview surface |surface_flow_su2AFLRTest.vtu |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.52098 Cd = 0.020148
Projecting tessellation 1 (of 4) on to new body
Projecting tessellation 2 (of 4) on to new body
Projecting tessellation 3 (of 4) on to new body
Projecting tessellation 4 (of 4) on to new body
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wake
Boundary condition name - Wing1
Boundary condition name - Wing2
Done getting CFD boundary conditions
Writing SU2 surface file
Writing SU2 Motion File - su2AFLRTest_motion.dat
Writing boundary flags
- bcProps.surfaceProp[0].surfaceType = 3
- bcProps.surfaceProp[1].surfaceType = 15
- bcProps.surfaceProp[2].surfaceType = 1
- bcProps.surfaceProp[3].surfaceType = 1
Done boundary flags
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Harrier (8.0.0) "
Mesh Morphing......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Mesh Deformation Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: aflr3_0.su2
---------------- Grid deformation parameters ( Zone 0 ) ----------------
Grid deformation using a linear elasticity method.
-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aflr3_0.su2.
Cell stiffness scaled by distance to nearest solid surface.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
| | BC_2|
+-----------------------------------------------------------------------+
| Far-field| BC_4|
+-----------------------------------------------------------------------+
| Internal boundary| BC_3|
+-----------------------------------------------------------------------+
Three dimensional problem.
55692 grid points.
306725 volume elements.
4 surface markers.
9958 boundary elements in index 0 (Marker = BC_1).
5414 boundary elements in index 1 (Marker = BC_2).
80 boundary elements in index 2 (Marker = BC_3).
420 boundary elements in index 3 (Marker = BC_4).
306725 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: 2.08667e+06.
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
Ignoring Convergence Field(s): RMS_DENSITY
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 5.459791 seconds on 1 core.
----------------------- Write deformed grid files -----------------------
|SU2 mesh |aflr3_0.su2 |
|CSV file |surface_deformed.csv |
|Paraview |volume_deformed.vtu |
|Paraview surface |surface_deformed.vtu |
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) ------------------------
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.5901.
Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 40 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 14.1421 m.
Surface(s) where the force coefficients are evaluated and
their reference origin for moment computation:
- BC_1 (0, 0, 0).
- BC_2 (0, 0, 0) m.
Surface(s) plotted in the output file: BC_1, BC_2.
Surface(s) affected by the design variables: BC_1, BC_2.
Input mesh file name: aflr3_0.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 10.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-8.
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|
| PARAVIEW| 250|
| SURFACE_PARAVIEW| 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_su2AFLRTest.dat.
Surface file name: surface_flow_su2AFLRTest.
Volume file name: flow_su2AFLRTest.
Restart file name: restart_flow_su2AFLRTest.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
| | BC_2|
+-----------------------------------------------------------------------+
| Far-field| BC_4|
+-----------------------------------------------------------------------+
| Internal boundary| BC_3|
+-----------------------------------------------------------------------+
-------------------- 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.
55692 grid points.
306725 volume elements.
4 surface markers.
9958 boundary elements in index 0 (Marker = BC_1).
5414 boundary elements in index 1 (Marker = BC_2).
80 boundary elements in index 2 (Marker = BC_3).
420 boundary elements in index 3 (Marker = BC_4).
306725 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: 2.08667e+06.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 5523.56. Mean K: 58.7619. Standard deviation K: 282.437.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 17.5434| 84.9572|
| CV Face Area Aspect Ratio| 1.03956| 11174.7|
| CV Sub-Volume Ratio| 1.03737| 76809.1|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 55692| 1/1.00| 10|
| 1| 9209| 1/6.05| 8.23312|
| 2| 1415| 1/6.51| 6.6146|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.07107 m.
Wetted area = 95.6308 m^2.
Area projection in the x-plane = 9.17945 m^2, y-plane = 4.04295 m^2, z-plane = 44.962 m^2.
Max. coordinate in the x-direction = 12.3585 m, y-direction = 7.07107 m, z-direction = 0.521791 m.
Min. coordinate in the x-direction = 0 m, y-direction = -7.07107 m, z-direction = -0.400127 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Boundary marker BC_2 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 226952| 1| m^2/s^2| 226952|
| Velocity-X| 200.779| 1| m/s| 200.779|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 3.50461| 1| m/s| 3.50461|
| Velocity Magnitude| 200.809| 1| m/s| 200.809|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.5901|
+------------------------------------------------------------------------------+
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| 1.1894e+00| -0.395911| 1.980314| 1.646923| 5.094985| 1.913176|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.0801e+00| -0.263244| 2.226198| 1.949589| 5.238568| 2.547049|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.0540e+00| -0.208348| 2.309357| 2.198185| 5.285085| 3.914397|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.0309e+00| -0.234717| 2.345148| 2.348550| 5.245683| 5.879161|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.0231e+00| -0.273135| 2.359089| 2.421633| 5.194487| 7.767865|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.0270e+00| -0.284384| 2.368405| 2.446997| 5.189344| 9.270982|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.0315e+00| -0.294753| 2.363090| 2.455733| 5.191507| 10.462882|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.0330e+00| -0.319538| 2.340251| 2.466131| 5.173062| 11.320106|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.0359e+00| -0.349768| 2.292885| 2.471955| 5.137977| 11.778124|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.0379e+00| -0.372277| 2.234008| 2.463003| 5.106430| 11.856729|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.372277| < -8| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_su2AFLRTest.dat |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|CSV file |surface_flow_su2AFLRTest.csv |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview |flow_su2AFLRTest.vtu |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview surface |surface_flow_su2AFLRTest.vtu |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.883374 Cd = 0.074504
real 0m56.037s
user 0m49.126s
sys 0m1.731s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_Morph_PyTest.py passed (as expected)
=================================================
delaundo: /Users/jenkins/util/delaundo/delaundo/src/delaundo
=================================================
+ echo 'su2_and_Delaundo_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
su2_and_Delaundo_PyTest.py test;
+ python -u su2_and_Delaundo_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = 2DSlice, index = 1
Name = TunnelWall, index = 2
Name = OutFlow, index = 3
Name = InFlow, index = 4
Name = Airfoil, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 5
Name = 2DSlice, index = 1
Name = TunnelWall, index = 2
Name = OutFlow, index = 3
Name = InFlow, index = 4
Name = Airfoil, index = 5
Getting mesh sizing parameters
Mesh sizing name - 2DSlice
Mesh sizing name - Airfoil
Mesh sizing name - InFlow
Mesh sizing name - OutFlow
Mesh sizing name - TunnelWall
Done getting mesh sizing parameters
Getting edge discretization for body 1
Delaundo expects 2D meshes be in the x-y plane... attempting to rotate mesh through node swapping!
Swapping z and y coordinates!
Writing delaundo control file - delaundo.ctr
Writing out *.pts file
Reading delaundo mesh file - delaundoMesh.mesh
Swapping y and z coordinates!
Writing TECPLOT file: delaundoMesh.dat ....
Finished writing TECPLOT file
Writing SU2 file ....
SU2 expects 2D meshes be in the x-y plane... attempting to rotate mesh!
Swapping z and y coordinates!
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Airfoil
Boundary condition name - InFlow
Boundary condition name - OutFlow
Boundary condition name - TunnelWall
Warning: No boundary condition specified for capsGroup 2DSlice!
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Harrier (8.0.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.4.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_5.
Surface(s) plotted in the output file: BC_5, BC_2.
Input mesh file name: ../delaundo/delaundoMesh.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: 10.
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_delaundoMesh.dat.
Surface file name: surface_flow_delaundoMesh.
Volume file name: flow_delaundoMesh.
Restart file name: restart_flow_delaundoMesh.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_5|
| | BC_2|
+-----------------------------------------------------------------------+
| Inlet boundary| BC_4|
+-----------------------------------------------------------------------+
| Outlet boundary| BC_3|
+-----------------------------------------------------------------------+
-------------------- 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 ) -------------------
Two dimensional problem.
6317 grid points.
12340 volume elements.
5 surface markers.
24 boundary elements in index 0 (Marker = BC_2).
24 boundary elements in index 1 (Marker = BC_3).
24 boundary elements in index 2 (Marker = BC_2).
24 boundary elements in index 3 (Marker = BC_4).
198 boundary elements in index 4 (Marker = BC_5).
12340 triangles.
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.
There has been a re-orientation of 294 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 999.917.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 1792.95. Mean K: 10.8142. Standard deviation K: 104.33.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 45.3524| 89.2595|
| CV Face Area Aspect Ratio| 1.03245| 15.7138|
| CV Sub-Volume Ratio| 1| 7.93643|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 6317| 1/1.00| 10|
| 1| 1792| 1/3.53| 7.98923|
| 2| 509| 1/3.52| 6.38684|
+-------------------------------------------+
Finding max control volume width.
Wetted area = 2.07206 m.
Area projection in the x-plane = 0.179342 m, y-plane = 1.00053 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.138492 m.
Min. coordinate in the x-direction = -0.00104578 m, y-direction = -0.0151891 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_5 is NOT a single straight.
Boundary marker BC_2 is a single straight.
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| 216054| 1| m^2/s^2| 216054|
| Velocity-X| 136.119| 1| m/s| 136.119|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity Magnitude| 136.119| 1| m/s| 136.119|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.4|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.8136e-02| -1.163068| 1.073873| 1.341547| 4.312268| 0.062082|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.7714e-02| -1.558471| 0.813117| 0.969484| 3.926501| 0.143132|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.7379e-02| -1.599269| 0.950037| 1.012154| 3.879885| 0.386300|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.7039e-02| -1.661284| 1.005970| 1.023067| 3.797319| 0.981260|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.7923e-02| -1.658421| 1.009907| 0.965279| 3.792658| 2.399755|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 3.7563e-02| -1.630602| 0.996801| 0.859556| 3.833204| 6.390579|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 3.7326e-02| -1.628009| 1.002770| 0.822847| 3.846297| 27.872536|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 3.7995e-02| -1.646113| 1.024424| 0.882502| 3.830202| -48.293527|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 4.0363e-02| -1.672152| 1.033657| 0.939200| 3.797228| -22.113788|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 4.3829e-02| -1.695131| 1.018255| 0.944150| 3.765919| -19.281368|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.69513| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_delaundoMesh.dat |
Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
|CSV file |surface_flow_delaundoMesh.csv |
Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
|Tecplot binary |flow_delaundoMesh.szplt |
Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
|Tecplot binary surface |surface_flow_delaundoMesh.szplt |
Error in tecFileWriterClose: Not all node map values for zone 1 have been written.
Currently need 492 more values.0: Error finishing Tecplot file output.
Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.805707 Cd = -0.041787
Cmz = 0.408515
Cx = -0.041787 Cy = 0.805707
Pressure Contribution
Cl_p = 0.805707 Cd_p = -0.041787
Cmz_p = 0.408515
Cx_p = -0.041787 Cy_p = 0.805707
Viscous Contribution
Cl_v = 0.0 Cd_v = 0.0
Cmz_v = 0.0
Cx_v = 0.0 Cy_v = 0.0
real 0m1.929s
user 0m1.802s
sys 0m0.499s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_and_Delaundo_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'su2_and_Tetgen_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
su2_and_Tetgen_PyTest.py test;
+ python -u su2_and_Tetgen_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Getting surface mesh for body 1 (of 3)
Getting surface mesh for body 2 (of 3)
Getting surface mesh for body 3 (of 3)
Body 1 (of 3)
Number of nodes = 2236
Number of elements = 4468
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 4468
Number of quadrilateral elements = 0
Body 2 (of 3)
Number of nodes = 636
Number of elements = 1268
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 1268
Number of quadrilateral elements = 0
Body 3 (of 3)
Number of nodes = 258
Number of elements = 512
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 512
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3130
Total number of elements = 6248
Writing TECPLOT file: egadsTessMesh_Surf_0.dat ....
Finished writing TECPLOT file
Writing TECPLOT file: egadsTessMesh_Surf_1.dat ....
Finished writing TECPLOT file
Writing TECPLOT file: egadsTessMesh_Surf_2.dat ....
Finished writing TECPLOT file
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Number of surface: nodes - 3130, elements - 6248
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds: 0.042278
Creating surface mesh ...
Surface mesh seconds: 0.006246
Recovering boundaries...
Boundary recovery seconds: 0.106765
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds: 0.006065
Suppressing Steiner points ...
Steiner suppression seconds: 5e-06
Recovering Delaunayness...
Delaunay recovery seconds: 0.011129
Refining mesh...
4180 insertions, added 2061 points, 130359 tetrahedra in queue.
1391 insertions, added 425 points, 134059 tetrahedra in queue.
1855 insertions, added 465 points, 131734 tetrahedra in queue.
2472 insertions, added 531 points, 115562 tetrahedra in queue.
3296 insertions, added 526 points, 67935 tetrahedra in queue.
4393 insertions, added 433 points, 372 tetrahedra in queue.
5856 insertions, added 571 points, 794 tetrahedra in queue.
Refinement seconds: 1.01429
Smoothing vertices...
Mesh smoothing seconds: 0.660528
Improving mesh...
Mesh improvement seconds: 0.031591
Jettisoning redundant points.
Writing nodes.
Writing elements.
Writing faces.
Writing edges.
Output seconds: 0.002198
Total running seconds: 1.88136
Statistics:
Input points: 3130
Input facets: 6248
Input segments: 9372
Input holes: 2
Input regions: 0
Mesh points: 8154
Mesh tetrahedra: 40351
Mesh faces: 83827
Mesh faces on exterior boundary: 6250
Mesh faces on input facets: 6250
Mesh edges on input segments: 9373
Steiner points on input segments: 1
Steiner points inside domain: 5023
Done meshing using TetGen!
Volume mesher did not preserve surface elements - data transfer will NOT be possible.
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wing1
Boundary condition name - Wing2
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Harrier (8.0.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.5901.
Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 50 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 15.8114 m.
Surface(s) where the force coefficients are evaluated and
their reference origin for moment computation:
- BC_1 (0, 0, 0).
- BC_2 (0, 0, 0) m.
Surface(s) plotted in the output file: BC_1, BC_2.
Input mesh file name: ../myMesh/tetgen_0.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 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|
| PARAVIEW| 250|
| SURFACE_PARAVIEW| 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_pyCAPS_SU2_Tetgen.dat.
Surface file name: surface_flow_pyCAPS_SU2_Tetgen.
Volume file name: flow_pyCAPS_SU2_Tetgen.
Restart file name: restart_flow_pyCAPS_SU2_Tetgen.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
| | BC_2|
+-----------------------------------------------------------------------+
| Far-field| BC_3|
+-----------------------------------------------------------------------+
-------------------- 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.
8154 grid points.
40351 volume elements.
3 surface markers.
4468 boundary elements in index 0 (Marker = BC_1).
1270 boundary elements in index 1 (Marker = BC_2).
512 boundary elements in index 2 (Marker = BC_3).
40351 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: 2.08741e+06.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 414.134. Mean K: 30.6158. Standard deviation K: 37.5195.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 1.93303| 83.8522|
| CV Face Area Aspect Ratio| 1.66492| 8220.52|
| CV Sub-Volume Ratio| 1.0945| 249103|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 8154| 1/1.00| 10|
| 1| 1365| 1/5.97| 8.26695|
| 2| 222| 1/6.15| 6.76877|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.90569 m.
Wetted area = 120.046 m^2.
Area projection in the x-plane = 10.7914 m^2, y-plane = 4.5843 m^2, z-plane = 57.287 m^2.
Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.557773 m.
Min. coordinate in the x-direction = -0.00409054 m, y-direction = -7.90569 m, z-direction = -0.41192 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Boundary marker BC_2 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 226952| 1| m^2/s^2| 226952|
| Velocity-X| 200.779| 1| m/s| 200.779|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 3.50461| 1| m/s| 3.50461|
| Velocity Magnitude| 200.809| 1| m/s| 200.809|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.5901|
+------------------------------------------------------------------------------+
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| 1.1614e-01| 0.616284| 3.048260| 2.091357| 6.107180| 1.815389|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.2320e-01| 0.741001| 3.258088| 2.952168| 6.243294| 2.156707|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.2459e-01| 0.650783| 3.322878| 3.201040| 6.147243| 3.157692|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.2653e-01| 0.569960| 3.293032| 3.250810| 6.036360| 4.529265|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.2636e-01| 0.533226| 3.191940| 3.195181| 5.994483| 5.686317|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 0.533226| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_pyCAPS_SU2_Tetgen.dat |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
|CSV file |surface_flow_pyCAPS_SU2_Tetgen.csv |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
|Paraview |flow_pyCAPS_SU2_Tetgen.vtu |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
|Paraview surface |surface_flow_pyCAPS_SU2_Tetgen.vtu |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.757437 Cd = 0.133203
Cmx = -0.003663 Cmy = -0.214942 Cmz = 0.000732
Cx = 0.119964 Cy = 0.000385 Cz = 0.759646
real 0m6.099s
user 0m5.842s
sys 0m0.375s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_and_Tetgen_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'su2_X43a_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
su2_X43a_PyTest.py test;
+ python -u su2_X43a_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = x43A, index = 1
Name = Farfield, index = 2
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 0
Getting surface mesh for body 1 (of 2)
Getting surface mesh for body 2 (of 2)
Body 1 (of 2)
Number of nodes = 3801
Number of elements = 7602
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 7602
Number of quadrilateral elements = 0
Body 2 (of 2)
Number of nodes = 5678
Number of elements = 11352
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 11352
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 9479
Total number of elements = 18954
Writing TECPLOT file: egadsTessMesh_Surf_0.dat ....
Finished writing TECPLOT file
Writing TECPLOT file: egadsTessMesh_Surf_1.dat ....
Finished writing TECPLOT file
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = x43A, index = 1
Name = Farfield, index = 2
Number of surface: nodes - 9479, elements - 18954
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds: 0.11464
Creating surface mesh ...
Surface mesh seconds: 0.022455
Recovering boundaries...
Boundary recovery seconds: 0.243084
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds: 0.013744
Recovering Delaunayness...
Delaunay recovery seconds: 0.040067
Refining mesh...
12636 insertions, added 5271 points, 44 tetrahedra in queue.
Refinement seconds: 0.984908
Smoothing vertices...
Mesh smoothing seconds: 0.762282
Improving mesh...
Mesh improvement seconds: 0.044145
Jettisoning redundant points.
Writing nodes.
Writing elements.
Writing faces.
Writing edges.
Output seconds: 0.004959
Total running seconds: 2.23076
Statistics:
Input points: 9479
Input facets: 18954
Input segments: 28431
Input holes: 1
Input regions: 0
Mesh points: 14884
Mesh tetrahedra: 61455
Mesh faces: 132387
Mesh faces on exterior boundary: 18954
Mesh faces on input facets: 18954
Mesh edges on input segments: 28431
Steiner points inside domain: 5405
Done meshing using TetGen!
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - x43A
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "Harrier (8.0.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 3.5.
Angle of attack (AoA): 3 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.
Surface(s) plotted in the output file: BC_1.
Input mesh file name: ../myMesh/tetgen_0.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 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|
| PARAVIEW| 250|
| SURFACE_PARAVIEW| 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_x43a_Test.dat.
Surface file name: surface_flow_x43a_Test.
Volume file name: flow_x43a_Test.
Restart file name: restart_flow_x43a_Test.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.
14884 grid points.
61455 volume elements.
2 surface markers.
7602 boundary elements in index 0 (Marker = BC_1).
11352 boundary elements in index 1 (Marker = BC_2).
61455 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: 2.67745e+08.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 95.6599. Mean K: 0.525135. Standard deviation K: 2.58749.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 2.08531| 84.4135|
| CV Face Area Aspect Ratio| 1.31056| 2090.22|
| CV Sub-Volume Ratio| 1| 1.13144e+06|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 14884| 1/1.00| 10|
| 1| 2708| 1/5.5| 8.49965|
| 2| 490| 1/5.53| 7.21121|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 30 m.
Wetted area = 13592.9 m^2.
Area projection in the x-plane = 761.52 m^2, y-plane = 2060.65 m^2, z-plane = 5463.74 m^2.
Max. coordinate in the x-direction = 150 m, y-direction = 30 m, z-direction = 19 m.
Min. coordinate in the x-direction = 0 m, y-direction = -30 m, z-direction = -10.3 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| 916077| 1| m^2/s^2| 916077|
| Velocity-X| 1189.41| 1| m/s| 1189.41|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 62.3342| 1| m/s| 62.3342|
| Velocity Magnitude| 1191.04| 1| m/s| 1191.04|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 3.5|
+------------------------------------------------------------------------------+
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| 2.2931e-01| 2.731008| 5.665319| 4.731467| 8.730483| -0.401144|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.2355e-01| 3.170324| 6.219154| 5.698493| 9.178926| -0.118433|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.2885e-01| 3.293104| 6.361720| 5.746884| 9.254295| -0.044919|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 2.2532e-01| 3.250958| 6.318931| 5.673519| 9.221763| -0.034783|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.2478e-01| 3.162927| 6.214039| 5.564073| 9.142969| -0.051969|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 3.16293| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_x43a_Test.dat |
Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
|CSV file |surface_flow_x43a_Test.csv |
Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
|Paraview |flow_x43a_Test.vtu |
Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
|Paraview surface |surface_flow_x43a_Test.vtu |
Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
+-----------------------------------------------------------------------+
Warning: there are 129 non-physical points in the solution.
Warning: 57 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 Force - Pressure + Viscous
Cl = -5.94765 Cd = 114.445668
Cmx = -14.939628 Cmy = 9349.058596 Cmz = -28.196104
Cx = 114.6001 Cy = -0.864184 Cz = 0.050124
real 0m14.098s
user 0m19.775s
sys 0m0.583s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_X43a_PyTest.py passed (as expected)
=================================================
./execute_PyTestRegression.sh: line 415: ulimit: stack size: cannot modify limit: Operation not permitted
flowCart: /Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC//flowCart
=================================================
+ echo 'cart3d_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
cart3d_PyTest.py test;
+ python -u cart3d_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
Loading AIM
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Body size = 3.796888
Tessellating body 1 with MaxEdge = 0.094922 Sag = 0.003797 Angle = 15.000000
Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 9 > autoInputs.out
Executing: ./aero.csh > aero.out
C_A 0.023693377
C_Y -0.0012129281
C_N 0.065395002
C_D 0.025961197
C_S -0.0012129281
C_L 0.064528278
C_l 0.0510971
C_m 0.000248187
C_n -0.017525
C_M_x 0.0504544
C_M_y 0.000248187
C_M_z -0.0192976
real 0m22.539s
user 0m27.565s
sys 0m1.137s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case cart3d_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'cart3d_OpenMDAO_3_alpha_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
cart3d_OpenMDAO_3_alpha_PyTest.py test;
+ python -u cart3d_OpenMDAO_3_alpha_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
----------------------------------------
>>> alpha [2.]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Getting CFD design variables.......
Number of design variables - 1
Design Variable name - alpha
Done getting CFD design variables
Getting CFD functional.......
Number of design variables - 1
Objective name - CL2
Done getting CFD functional
Body size = 3.625615
Tessellating body 1 with MaxEdge = 0.090640 Sag = 0.003626 Angle = 15.000000
Executing: autoInputs -r 30.000000 -nDiv 5 -maxR 7 -mesh2d > autoInputs.out
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:20:19) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1
(00:20:23) aero.csh done
o case M0.5901A2B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.01631562] CL 0.12773309
----------------------------------------
----------------------------------------
>>> alpha [2.]
>>> CL2 [0.01631562] CL 0.12773309
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:20:24) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1
(00:20:28) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 2188
Estimated cutter memory: 0.000219 GB / DV
Estimated xsensit memory: 0.004157 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:20:29) Linearizing cut-cells
(00:20:29) ... done
o Number of simultaneous xsensit jobs: 1
(00:20:29) Computing gradients
(00:20:33) ... done
o case M0.5901A2B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[0.01572627]]
========================================
RUNNING THE L-BFGS-B CODE
* * *
Machine precision = 2.220D-16
N = 1 M = 10
At X0 0 variables are exactly at the bounds
At iterate 0 f= 1.63156D-02 |proj g|= 1.57263D-02
----------------------------------------
>>> alpha [1.98427373]
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:20:34) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1
(00:20:38) aero.csh done
o case M0.5901A1.98427B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.01606724] CL 0.12675617
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:20:39) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1
(00:20:45) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 2188
Estimated cutter memory: 0.000219 GB / DV
Estimated xsensit memory: 0.004157 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:20:46) Linearizing cut-cells
(00:20:46) ... done
o Number of simultaneous xsensit jobs: 1
(00:20:46) Computing gradients
(00:20:50) ... done
o case M0.5901A1.98427B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[0.01560329]]
========================================
At iterate 1 f= 1.60672D-02 |proj g|= 1.56033D-02
----------------------------------------
>>> alpha [-0.01099175]
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:20:51) Running aero.csh on 2 core(s) in M0.5901A-0.0109917B0_DP1
(00:20:54) aero.csh done
o case M0.5901A-0.0109917B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [6.05653711e-06] CL 0.00246101
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:20:55) Running aero.csh on 2 core(s) in M0.5901A-0.0109917B0_DP1
(00:20:59) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 2188
Estimated cutter memory: 0.000219 GB / DV
Estimated xsensit memory: 0.004157 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:20:59) Linearizing cut-cells
(00:20:59) ... done
o Number of simultaneous xsensit jobs: 1
(00:20:59) Computing gradients
(00:21:03) ... done
o case M0.5901A-0.0109917B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[0.00031042]]
========================================
At iterate 2 f= 6.05654D-06 |proj g|= 3.10424D-04
----------------------------------------
>>> alpha [-0.05149286]
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:21:04) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1
(00:21:08) aero.csh done
o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [2.59817062e-10] CL 1.612e-05
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:21:09) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1
(00:21:12) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 2188
Estimated cutter memory: 0.000219 GB / DV
Estimated xsensit memory: 0.004157 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:21:13) Linearizing cut-cells
(00:21:13) ... done
o Number of simultaneous xsensit jobs: 1
(00:21:13) Computing gradients
(00:21:17) ... done
o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[2.03612433e-06]]
========================================
At iterate 3 f= 2.59817D-10 |proj g|= 2.03612D-06
----------------------------------------
>>> alpha [-0.05176027]
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:21:18) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1
(00:21:21) aero.csh done
o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [9.25766089e-15] CL 1e-07
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:21:22) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1
(00:21:26) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 2188
Estimated cutter memory: 0.000219 GB / DV
Estimated xsensit memory: 0.004157 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:21:26) Linearizing cut-cells
(00:21:26) ... done
o Number of simultaneous xsensit jobs: 1
(00:21:26) Computing gradients
(00:21:30) ... done
o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[1.21372408e-08]]
========================================
At iterate 4 f= 9.25766D-15 |proj g|= 1.21372D-08
* * *
Tit = total number of iterations
Tnf = total number of function evaluations
Tnint = total number of segments explored during Cauchy searches
Skip = number of BFGS updates skipped
Nact = number of active bounds at final generalized Cauchy point
Projg = norm of the final projected gradient
F = final function value
* * *
N Tit Tnf Tnint Skip Nact Projg F
1 4 5 4 0 0 1.214D-08 9.258D-15
F = 9.2576608860000000E-015
CONVERGENCE: NORM_OF_PROJECTED_GRADIENT_<=_PGTOL
Optimization Complete
-----------------------------------
Optimized value: [-0.05176027]
real 1m17.094s
user 0m53.460s
sys 0m9.106s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case cart3d_OpenMDAO_3_alpha_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'cart3d_OpenMDAO_3_twist_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
cart3d_OpenMDAO_3_twist_PyTest.py test;
+ python -u cart3d_OpenMDAO_3_twist_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
----------------------------------------
>>> twist [4.]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Getting CFD design variables.......
Number of design variables - 1
Design Variable name - twist
Done getting CFD design variables
Getting CFD functional.......
Number of design variables - 1
Objective name - CL2
Done getting CFD functional
Body size = 3.630958
Tessellating body 1 with MaxEdge = 0.018155 Sag = 0.000908 Angle = 10.000000
Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:21:35) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:21:51) aero.csh done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.00411365] CL 0.0641354
----------------------------------------
----------------------------------------
>>> twist [4.]
>>> CL2 [0.00411365] CL 0.0641354
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:21:52) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:22:13) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 37528
Estimated cutter memory: 0.003753 GB / DV
Estimated xsensit memory: 0.071303 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:22:13) Linearizing cut-cells
(00:22:15) ... done
o Number of simultaneous xsensit jobs: 1
(00:22:15) Computing gradients
(00:22:19) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[0.00210056]]
========================================
RUNNING THE L-BFGS-B CODE
* * *
Machine precision = 2.220D-16
N = 1 M = 10
At X0 0 variables are exactly at the bounds
At iterate 0 f= 4.11365D-03 |proj g|= 2.10056D-03
----------------------------------------
>>> twist [3.99789944]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Body size = 3.630955
Tessellating body 1 with MaxEdge = 0.018155 Sag = 0.000908 Angle = 10.000000
Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:22:23) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:22:46) aero.csh done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.0041123] CL 0.0641197
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:22:48) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:23:19) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 37527
Estimated cutter memory: 0.003753 GB / DV
Estimated xsensit memory: 0.071301 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:23:20) Linearizing cut-cells
(00:23:22) ... done
o Number of simultaneous xsensit jobs: 1
(00:23:22) Computing gradients
(00:23:26) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[0.00210014]]
========================================
At iterate 1 f= 4.11230D-03 |proj g|= 2.10014D-03
----------------------------------------
>>> twist [-6.51746917]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Body size = 3.635732
Tessellating body 1 with MaxEdge = 0.018179 Sag = 0.000909 Angle = 10.000000
Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:23:30) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:23:44) aero.csh done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.00998116] CL -0.099904
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:23:45) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:24:03) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 37089
Estimated cutter memory: 0.003709 GB / DV
Estimated xsensit memory: 0.070469 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:24:04) Linearizing cut-cells
(00:24:06) ... done
o Number of simultaneous xsensit jobs: 1
(00:24:06) Computing gradients
(00:24:10) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[-0.003197]]
========================================
----------------------------------------
>>> twist [-0.14353734]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Body size = 3.625762
Tessellating body 1 with MaxEdge = 0.018129 Sag = 0.000906 Angle = 10.000000
Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:24:13) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:24:26) aero.csh done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [6.66922068e-08] CL -0.00023482
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:24:27) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:24:45) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 37755
Estimated cutter memory: 0.003776 GB / DV
Estimated xsensit memory: 0.071735 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:24:46) Linearizing cut-cells
(00:24:48) ... done
o Number of simultaneous xsensit jobs: 1
(00:24:48) Computing gradients
(00:24:52) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[-8.54769827e-06]]
========================================
At iterate 2 f= 6.66922D-08 |proj g|= 8.54770D-06
----------------------------------------
>>> twist [-0.12674977]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Body size = 3.625744
Tessellating body 1 with MaxEdge = 0.018129 Sag = 0.000906 Angle = 10.000000
Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:24:55) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:25:12) aero.csh done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [5.57225179e-09] CL 0.00010424
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:25:13) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:25:38) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 37755
Estimated cutter memory: 0.003776 GB / DV
Estimated xsensit memory: 0.071735 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(00:25:38) Linearizing cut-cells
(00:25:40) ... done
o Number of simultaneous xsensit jobs: 1
(00:25:40) Computing gradients
(00:25:44) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[2.47231508e-06]]
========================================
At iterate 3 f= 5.57225D-09 |proj g|= 2.47232D-06
* * *
Tit = total number of iterations
Tnf = total number of function evaluations
Tnint = total number of segments explored during Cauchy searches
Skip = number of BFGS updates skipped
Nact = number of active bounds at final generalized Cauchy point
Projg = norm of the final projected gradient
F = final function value
* * *
N Tit Tnf Tnint Skip Nact Projg F
1 3 5 3 0 0 2.472D-06 5.572D-09
F = 5.5722517919000003E-009
CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH
Optimization Complete
-----------------------------------
Optimized values: [-0.12674977]
real 4m13.917s
user 5m9.726s
sys 0m13.608s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case cart3d_OpenMDAO_3_twist_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'fun3d_Morph_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
fun3d_Morph_PyTest.py test;
+ python -u fun3d_Morph_PyTest.py -outLevel=0 -noAnalysis
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
AFLR4 : Proximity BG Surface Grid Generation Skipped
AFLR4 : No Modifications Required
Writing TECPLOT file: pyCAPS_AFLR4_AFLR3.dat ....
Finished writing TECPLOT file
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Getting volume mesh
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.7
AFLR2 : Version Date 07/16/23 @ 01:42PM
AFLR2 : Compile OS Darwin 22.6.0 arm64
AFLR2 : Compile Date 08/01/23 @ 11:39PM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR4 : ---------------------------------------
AFLR4 : AFLR4 LIBRARY
AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4 : Version Number 11.5.9
AFLR4 : Version Date 08/14/23 @ 12:27AM
AFLR4 : Compile OS Darwin 22.6.0 arm64
AFLR4 : Compile Date 08/14/23 @ 12:31AM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.7.0
EGADS : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.24
EGADS : OpenCASCADE Version 7.7.0
EGADS : ---------------------------------------
Volume mesh:
Number of nodes = 81189
Number of elements = 474220
Number of triangles = 15680
Number of quadrilatarals = 0
Number of tetrahedrals = 458540
Number of pyramids = 0
Number of prisms = 0
Number of hexahedrals = 0
Writing TECPLOT file: pyCAPS_AFLR4_AFLR3_VolMesh.dat ....
Finished writing TECPLOT file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wing1
Boundary condition name - Wing2
Done getting CFD boundary conditions
Getting CFD design variables.......
Number of design variables - 2
Design Variable name - Alpha
Design Variable name - twist
Done getting CFD design variables
Getting CFD functional.......
Number of design variables - 2
Objective name - Cd2
Objective name - Const
Done getting CFD functional
Python library was linked, but will not be used!
Creating FUN3D directory tree
DesignVariable = Alpha
DesignVariable = twist
Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1
Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1
Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1
Writing rubber.data
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing MAPBC file ....
Finished writing MAPBC file
Warning: The fun3d.nml file will be overwritten!
Writing fun3d.nml
Info: No recognized data transfer names found.
Reading rubber.data
Projecting tessellation 1 (of 3) on to new body
Projecting tessellation 2 (of 3) on to new body
Projecting tessellation 3 (of 3) on to new body
Python library was linked, but will not be used!
Creating FUN3D directory tree
DesignVariable = Alpha
DesignVariable = twist
Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1
Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1
Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing MAPBC file ....
Finished writing MAPBC file
Warning: The fun3d.nml file will be overwritten!
Writing fun3d.nml
Info: No recognized data transfer names found.
Reading rubber.data
real 0m14.522s
user 0m9.467s
sys 0m0.442s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case fun3d_Morph_PyTest.py passed (as expected)
=================================================
*************************************************
*************************************************
=================================================
Did not run examples for:
Fun3D
=================================================
All tests pass!
=================================================
=================================================
[GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64')
[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_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64')
[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_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64')
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.7/CAPS/CFD/DARWIN_ARM64')
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.7,CAPS/CFD,DARWIN_ARM64,viggen)
[Static Analysis] Using reference build 'ESP_UndefinedCaps/CASREV=7.7,ESPTEST=CAPS/CFD,ESP_ARCH=DARWIN_ARM64,buildnode=viggen #191' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1
[Static Analysis] -> All quality gates have been passed
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_UndefinedCaps/CASREV=7.7,ESPTEST=CAPS/CFD,ESP_ARCH=DARWIN_ARM64,buildnode=viggen #192'.
[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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