| 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_inviscidWing.dat.
Surface file name: surface_flow_inviscidWing.
Volume file name: flow_inviscidWing.
Restart file name: restart_flow_inviscidWing.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.
146357 grid points.
826860 volume elements.
2 surface markers.
25828 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
826860 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 5.96352e+10.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 25.1444. Mean K: 1.31911. Standard deviation K: 3.07302.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 52.8789| 87.0788|
| CV Face Area Aspect Ratio| 1.02024| 134.818|
| CV Sub-Volume Ratio| 1.04253| 1008|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 146357| 1/1.00| 10|
| 1| 24022| 1/6.09| 8.21277|
| 2| 3692| 1/6.51| 6.5988|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 97.6729 m.
Wetted area = 8686.36 m^2.
Area projection in the x-plane = 678.35 m^2, y-plane = 443.236 m^2, z-plane = 4164.26 m^2.
Max. coordinate in the x-direction = 127.552 m, y-direction = 97.6729 m, z-direction = 7.71806 m.
Min. coordinate in the x-direction = 54 m, y-direction = -97.6729 m, z-direction = -5.47911 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 221265| 1| m^2/s^2| 221265|
| Velocity-X| 170.123| 1| m/s| 170.123|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 2.9695| 1| m/s| 2.9695|
| Velocity Magnitude| 170.149| 1| m/s| 170.149|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.5|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 7.8518e+00| 0.938580| 3.215149| 2.934655| 6.421425| -0.381631|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 7.5901e+00| 1.004374| 3.477362| 3.113650| 6.501703| 0.082195|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 7.5357e+00| 1.107363| 3.624764| 3.405407| 6.593819| 1.629831|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 7.0247e+00| 1.179786| 3.742454| 3.581233| 6.658379| 7.056295|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 6.6923e+00| 1.257220| 3.830490| 3.677659| 6.742493| 38.919402|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 1.25722| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_inviscidWing.dat |
Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
|CSV file |surface_flow_inviscidWing.csv |
Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
|Paraview |flow_inviscidWing.vtu |
Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
|Paraview surface |surface_flow_inviscidWing.vtu |
Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
==> Total Forces and Moments
--> Cl = 0.321007 Cd = 0.008248
--> Cmx = -0.000149 Cmy = -0.052642 Cmz = 8.2e-05
--> Cx = 0.002644 Cy = 0.000155 Cz = 0.321102
real 1m15.852s
user 1m11.589s
sys 0m2.830s
+ status=0
+ set +x
=================================================
data/session08/su2_1_InviscidWing.py passed (as expected)
=================================================
=================================================
tess_1_Geom.py test;
+ python tess_1_Geom.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
real 0m24.011s
user 1m12.116s
sys 2m42.956s
+ status=0
+ set +x
=================================================
data/session09/tess_1_Geom.py passed (as expected)
=================================================
=================================================
tess_2_TFI_Templates.py test;
+ python tess_2_TFI_Templates.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 11058
Number of elements = 22735
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 22735
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 11058
Total number of elements = 22735
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 11915
Number of elements = 24449
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 24449
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 11915
Total number of elements = 24449
real 0m24.538s
user 1m22.767s
sys 2m45.193s
+ status=0
+ set +x
=================================================
data/session09/tess_2_TFI_Templates.py passed (as expected)
=================================================
=================================================
tess_3_Params.py test;
+ python tess_3_Params.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 731
Number of elements = 1779
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 1779
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 731
Total number of elements = 1779
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 940
Number of elements = 2240
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 2240
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 940
Total number of elements = 2240
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 3543
Number of elements = 7661
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 7661
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3543
Total number of elements = 7661
real 0m24.152s
user 1m16.445s
sys 2m22.059s
+ status=0
+ set +x
=================================================
data/session09/tess_3_Params.py passed (as expected)
=================================================
=================================================
tess_4_Params.py test;
+ python tess_4_Params.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 1399
Number of elements = 3122
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 3122
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 1399
Total number of elements = 3122
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 2096
Number of elements = 4573
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 4573
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 2096
Total number of elements = 4573
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 6575
Number of elements = 13719
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 13719
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 6575
Total number of elements = 13719
real 0m22.545s
user 1m17.932s
sys 2m42.496s
+ status=0
+ set +x
=================================================
data/session09/tess_4_Params.py passed (as expected)
=================================================
=================================================
tess_5_Params.py test;
+ python tess_5_Params.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 3548
Number of elements = 7437
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 7437
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3548
Total number of elements = 7437
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 12429
Number of elements = 25326
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 25326
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 12429
Total number of elements = 25326
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 45308
Number of elements = 91283
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 91283
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 45308
Total number of elements = 91283
real 0m29.673s
user 1m40.779s
sys 2m40.388s
+ status=0
+ set +x
=================================================
data/session09/tess_5_Params.py passed (as expected)
=================================================
=================================================
tess_6_TriQuad.py test;
+ python tess_6_TriQuad.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 8266
Number of elements = 17115
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 17115
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 8266
Total number of elements = 17115
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 72029
Number of elements = 74322
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 74322
----------------------------
Total number of nodes = 72029
Total number of elements = 74322
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 1566
Number of elements = 3043
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 3043
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 1566
Total number of elements = 3043
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 3009
Number of elements = 2928
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 2928
----------------------------
Total number of nodes = 3009
Total number of elements = 2928
real 0m53.450s
user 1m35.598s
sys 1m35.224s
+ status=0
+ set +x
=================================================
data/session09/tess_6_TriQuad.py passed (as expected)
=================================================
=================================================
tess_7_MeshSizing.py test;
+ python tess_7_MeshSizing.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 8266
Number of elements = 17115
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 17115
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 8266
Total number of elements = 17115
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting mesh sizing parameters
Mesh sizing name - leadingEdge
Mesh sizing name - rootLeadingEdge
Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 3860
Number of elements = 8288
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 8288
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3860
Total number of elements = 8288
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting mesh sizing parameters
Mesh sizing name - leadingEdge
Mesh sizing name - rootLeadingEdge
Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 6181
Number of elements = 6607
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 6607
----------------------------
Total number of nodes = 6181
Total number of elements = 6607
real 0m31.845s
user 1m13.568s
sys 1m48.241s
+ status=0
+ set +x
=================================================
data/session09/tess_7_MeshSizing.py passed (as expected)
=================================================
=================================================
tess_8_MeshSizing.py test;
+ python tess_8_MeshSizing.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 1566
Number of elements = 3043
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 3043
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 1566
Total number of elements = 3043
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting mesh sizing parameters
Mesh sizing name - rootLeadingEdge
Mesh sizing name - wingSpar1
Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 6582
Number of elements = 13186
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 13186
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 6582
Total number of elements = 13186
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting mesh sizing parameters
Mesh sizing name - rootLeadingEdge
Mesh sizing name - wingSpar1
Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 22194
Number of elements = 22195
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 22195
----------------------------
Total number of nodes = 22194
Total number of elements = 22195
real 0m27.909s
user 1m11.326s
sys 1m15.590s
+ status=0
+ set +x
=================================================
data/session09/tess_8_MeshSizing.py passed (as expected)
=================================================
=================================================
tess_MinQuad.py test;
+ python tess_MinQuad.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../../data/ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 299
Number of elements = 387
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 387
----------------------------
Total number of nodes = 299
Total number of elements = 387
--> Total Elements 387
real 0m23.544s
user 1m10.455s
sys 2m41.828s
+ status=0
+ set +x
=================================================
solutions/session09/tess_MinQuad.py passed (as expected)
=================================================
=================================================
tess_2k.py test;
+ python tess_2k.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../../data/ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting mesh sizing parameters
Mesh sizing name - rootLeadingEdge
Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 1289
Number of elements = 1189
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 1189
----------------------------
Total number of nodes = 1289
Total number of elements = 1189
--> Total Elements 1189
real 0m23.120s
user 1m2.816s
sys 1m36.922s
+ status=0
+ set +x
=================================================
solutions/session09/tess_2k.py passed (as expected)
=================================================
=================================================
astros_1_ModalClamped.py test;
+ python astros_1_ModalClamped.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 235
Number of elements = 227
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes = 235
Total number of elements = 227
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 235
Number of elements = 227
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Load tuple is NULL - No loads applied
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Getting FEA analyses.......
Number of analyses - 1
Analysis name - EigenAnalysis
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!!
Writing analysis cards
Writing constraint cards--all constraints for each subcase
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
Reading Astros OUT file - extracting Eigen-Values!
Number of Eigen-Values = 9
Loading Eigen-Value = 1
Loading Eigen-Value = 2
Loading Eigen-Value = 3
Loading Eigen-Value = 4
Loading Eigen-Value = 5
Loading Eigen-Value = 6
Loading Eigen-Value = 7
Loading Eigen-Value = 8
Loading Eigen-Value = 9
--> Eigen-frequencies:
1 : 0.0357647
2 : 0.102451
3 : 0.102451
4 : 0.159637
5 : 0.159637
6 : 0.215446
7 : 0.215446
8 : 0.350115
9 : 0.350115
real 0m23.719s
user 1m7.470s
sys 2m19.378s
+ status=0
+ set +x
=================================================
data/session10/astros_1_ModalClamped.py passed (as expected)
=================================================
=================================================
astros_2_ModalSupport.py test;
+ python astros_2_ModalSupport.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Name = ribSupport, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 2)
Getting surface mesh for body 2 (of 2)
Body 1 (of 2)
Number of nodes = 235
Number of elements = 227
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 227
Body 2 (of 2)
Number of nodes = 1
Number of elements = 1
Number of node elements = 1
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 236
Total number of elements = 228
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = ribRootPoint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 1
Name = ribRoot, index = 1
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Name = ribSupport, index = 6
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 235
Number of elements = 227
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 227
Setting FEA Data
Mesh for body = 1
Number of nodal coordinates = 1
Number of elements = 1
Elemental Nodes = 1
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 0
Combining multiple FEA meshes!
Combined Number of nodal coordinates = 236
Combined Number of elements = 228
Combined Elemental Nodes = 1
Combined Elemental Rods = 0
Combined Elemental Tria3 = 0
Combined Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 6
Property name - leftWingSkin
Property name - ribSupport
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - ribRootPoint
No "constraintType" specified for Constraint tuple ribRootPoint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple ribRootPoint, going to use constraint name
Done getting FEA constraints
Getting FEA supports.......
Number of supports - 1
Support name - ribRootPoint
No "groupName" specified for Support tuple ribRootPoint, going to use support name
Done getting FEA supports
Getting FEA connections.......
Number of connection tuples - 1
Connection name - ribRoot
No "groupName" specified for Connection tuple ribRoot!
Looking for automatic connections from the use of capsConnectLink for ribRoot
19 automatic connections were made for capsConnect ribRoot (node id 236)
Done getting FEA connections
Load tuple is NULL - No loads applied
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Getting FEA analyses.......
Number of analyses - 1
Analysis name - EigenAnalysis
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing connection cards - appending mesh file
Writing Astros instruction file....
Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!!
Writing analysis cards
Writing constraint cards--all constraints for each subcase
Writing support cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
Reading Astros OUT file - extracting Eigen-Values!
Number of Eigen-Values = 10
Loading Eigen-Value = 1
Loading Eigen-Value = 2
Loading Eigen-Value = 3
Loading Eigen-Value = 4
Loading Eigen-Value = 5
Loading Eigen-Value = 6
Loading Eigen-Value = 7
Loading Eigen-Value = 8
Loading Eigen-Value = 9
Loading Eigen-Value = 10
--> Eigen-frequencies:
1 : 0.0
2 : 0.0357647
3 : 0.0365801
4 : 0.102451
5 : 0.102453
6 : 0.159637
7 : 0.1611
8 : 0.215446
9 : 0.215462
10: 0.350115
real 0m25.009s
user 0m53.483s
sys 1m39.083s
+ status=0
+ set +x
=================================================
data/session10/astros_2_ModalSupport.py passed (as expected)
=================================================
=================================================
astros_3_StaticClamped.py test;
+ python astros_3_StaticClamped.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 235
Number of elements = 227
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes = 235
Total number of elements = 227
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 235
Number of elements = 227
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 2
Load name - leftPointLoad
No "groupName" specified for Load tuple leftPointLoad, going to use load name
Load name - ritePointLoad
No "groupName" specified for Load tuple ritePointLoad, going to use load name
Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
--> Maximum displacements:
--> Tmax 43461.879146949635
--> T1max 738.595
--> T2max 3686.25
--> T3max 43363.8
real 0m26.444s
user 1m4.763s
sys 2m3.722s
+ status=0
+ set +x
=================================================
data/session10/astros_3_StaticClamped.py passed (as expected)
=================================================
=================================================
astros_4_Composite.py test;
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
+ python astros_4_Composite.py
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 235
Number of elements = 227
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes = 235
Total number of elements = 227
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 235
Number of elements = 227
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Aluminum
No "materialType" specified for Material tuple Aluminum, defaulting to "Isotropic"
Material name - Graphite_epoxy
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 2
Load name - leftPointLoad
No "groupName" specified for Load tuple leftPointLoad, going to use load name
Load name - ritePointLoad
No "groupName" specified for Load tuple ritePointLoad, going to use load name
Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
--> Maximum displacements:
--> Tmax 12131.654370141774
--> T1max 275.241
--> T2max 1005.74
--> T3max 12103.5
real 0m27.380s
user 0m55.217s
sys 1m17.475s
+ status=0
+ set +x
=================================================
data/session10/astros_4_Composite.py passed (as expected)
=================================================
=================================================
nastran_5_Flutter.py test;
+ python nastran_5_Flutter.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
==> Running Nastran pre-analysis...
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = Wing, index = 1
Name = wingSpar2, index = 2
Name = wingRib, index = 3
Name = riteWingSkin, index = 4
Name = wingSpar1, index = 5
Name = leftWingSkin, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 4)
Getting surface mesh for body 2 (of 4)
Getting surface mesh for body 3 (of 4)
Getting surface mesh for body 4 (of 4)
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
Body 1 (of 4)
Number of nodes = 11
Number of elements = 6
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 6
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
Body 2 (of 4)
Number of nodes = 11
Number of elements = 6
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 6
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
Body 3 (of 4)
Number of nodes = 11
Number of elements = 6
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 6
Body 4 (of 4)
Number of nodes = 939
Number of elements = 1094
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 1094
----------------------------
Total number of nodes = 972
Total number of elements = 1112
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = Wing, index = 1
Name = wingSpar2, index = 2
Name = wingRib, index = 3
Name = riteWingSkin, index = 4
Name = wingSpar1, index = 5
Name = leftWingSkin, index = 6
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 11
Number of elements = 6
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 6
Setting FEA Data
Mesh for body = 1
Number of nodal coordinates = 11
Number of elements = 6
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 6
Setting FEA Data
Mesh for body = 2
Number of nodal coordinates = 11
Number of elements = 6
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 6
Setting FEA Data
Mesh for body = 3
Number of nodal coordinates = 939
Number of elements = 1094
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 1094
Combining multiple FEA meshes!
Combined Number of nodal coordinates = 972
Combined Number of elements = 1112
Combined Elemental Nodes = 0
Combined Elemental Rods = 0
Combined Elemental Tria3 = 0
Combined Elemental Quad4 = 1112
Getting vortex lattice surface data
VLM surface name - upperWing
Done getting vortex lattice surface data
Getting FEA vortex lattice mesh
Surface 1: Number of points found for aero-spline = 108
Surface 2: Number of points found for aero-spline = 108
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Load tuple is NULL - No loads applied
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Design_Equation tuple is NULL - No design equations applied
Design_Table tuple is NULL - No design table constants applied
Design_Opt_Param tuple is NULL - No design optimization parameters applied
Design_Response tuple is NULL - No design responses applied
Design_Equation_Response tuple is NULL - No design equation responses applied
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Flutter
Done getting FEA analyses
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing subElement types (if any) - appending mesh file
Writing Nastran instruction file....
Warning: No loads specified for case Flutter!!!!
Writing aero card
Writing analysis cards
Writing constraint ADD cards
Writing constraint cards
Writing material cards
Writing property cards
Writing coordinate system cards
Writing aeroelastic cards
==> Running Nastran...
sh: 1: nastran: not found
real 0m31.791s
user 1m0.637s
sys 0m44.464s
+ status=0
+ set +x
=================================================
data/session10/nastran_5_Flutter.py passed (as expected)
=================================================
=================================================
aeroelastic_2_Iterative_SU2_Astros.py test;
+ python aeroelastic_2_Iterative_SU2_Astros.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
Information: Dynamic Loader for scribeWake.so not found
scribeWake.so: cannot open shared object file: No such file or directory
==> Running SU2 pre-analysis...
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Wing, index = 1
Name = Farfield, index = 2
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = leftWing, index = 1
Name = riteWing, index = 2
Name = Farfield, index = 3
Getting mesh sizing parameters
Mesh sizing name - Farfield
Mesh sizing name - leftWing
Mesh sizing name - riteWing
Done getting mesh sizing parameters
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.6
AFLR2 : Version Date 11/20/22 @ 09:21PM
AFLR2 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR2 : Compile Date 02/08/23 @ 12:48PM
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 11.3.17
AFLR4 : Version Date 03/03/23 @ 03:12PM
AFLR4 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR4 : Compile Date 03/03/23 @ 11:35PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.23
EGADS : OpenCASCADE Version 7.4.1
EGADS : ---------------------------------------
EGADS : EGADS CAD Geometry Setup
EGADS : Model has 2 Active Bodies
EGADS : Body 0 is a SolidBody
EGADS : Body 0 has 1 Shells
EGADS : Body 0 has 6 Faces
EGADS : Body 0 has 10 Edges
EGADS : Body 0 has 6 Loops
EGADS : Body 0 has 6 Nodes
EGADS : Body 1 is a SolidBody
EGADS : Body 1 has 1 Shells
EGADS : Body 1 has 6 Faces
EGADS : Body 1 has 12 Edges
EGADS : Body 1 has 6 Loops
EGADS : Body 1 has 8 Nodes
EGADS : Check Grid BCs
EGADS : Grid BCs are OK
EGADS : Face Neighbor-Faces Information
EGADS : QC = Face Quad Combination Flag
EGADS : IER = Face Isolated Edge Refinement Flag
EGADS : ER = Face Edge Refinement Factor
EGADS : Not applicable for Faces with a FarField Grid BC.
EGADS : SF = Face Scale Factor
EGADS : Not applicable for Faces with a FarField Grid BC.
EGADS : Face Body QC IER ER Scale Neighbor
EGADS : ID Active ID Flag Flag Weight Factor Faces
EGADS : 1 Yes 0 0 1 1 1 2 3 4
EGADS : 2 Yes 0 0 1 1 1 1 3 5
EGADS : 3 Yes 0 0 1 1 1 1 2
EGADS : 4 Yes 0 0 1 1 1 1 5 6
EGADS : 5 Yes 0 0 1 1 1 2 4 6
EGADS : 6 Yes 0 0 1 1 1 4 5
EGADS : 7 Yes 1 0 1 NA NA 9 10 11 12
EGADS : 8 Yes 1 0 1 NA NA 9 10 11 12
EGADS : 9 Yes 1 0 1 NA NA 7 8 11 12
EGADS : 10 Yes 1 0 1 NA NA 7 8 11 12
EGADS : 11 Yes 1 0 1 NA NA 7 8 9 10
EGADS : 12 Yes 1 0 1 NA NA 7 8 9 10
EGADS : Face Edges Information
EGADS : Face Edges
EGADS : 1 -1 2 3 -4
EGADS : 2 -3 5 1 -6
EGADS : 3 4 6
EGADS : 4 7 9 -8 -2
EGADS : 5 8 10 -7 -5
EGADS : 6 -9 -10
EGADS : 7 11 12 -13 -14
EGADS : 8 -15 18 17 -16
EGADS : 9 19 15 -20 -11
EGADS : 10 -21 13 22 -17
EGADS : 11 14 21 -18 -19
EGADS : 12 -12 20 16 -22
EGADS : Face Loops Information
EGADS : Face Loops
EGADS : 1 1
EGADS : 2 2
EGADS : 3 3
EGADS : 4 4
EGADS : 5 5
EGADS : 6 6
EGADS : 7 7
EGADS : 8 8
EGADS : 9 9
EGADS : 10 10
EGADS : 11 11
EGADS : 12 12
EGADS : Loop Edges Information
EGADS : Loop Active Sense Edges
EGADS : 1 Yes 1 -1 2 3 -4
EGADS : 2 Yes 1 -3 5 1 -6
EGADS : 3 Yes 1 4 6
EGADS : 4 Yes 1 7 9 -8 -2
EGADS : 5 Yes 1 8 10 -7 -5
EGADS : 6 Yes 1 -9 -10
EGADS : 7 Yes 1 11 12 -13 -14
EGADS : 8 Yes 1 -15 18 17 -16
EGADS : 9 Yes 1 19 15 -20 -11
EGADS : 10 Yes 1 -21 13 22 -17
EGADS : 11 Yes 1 14 21 -18 -19
EGADS : 12 Yes 1 -12 20 16 -22
EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information
EGADS : ESF = Edge Scale Factor
EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField
EGADS : Grid BC Neighbor Face.
EGADS : Neighbor
EGADS : Edge Body Active Node1 Node2 ESF Faces
EGADS : 1 0 Yes 1 2 1 1 2
EGADS : 2 0 Yes 1 3 1 1 4
EGADS : 3 0 Yes 3 4 1 1 2
EGADS : 4 0 Yes 2 4 1 1 3
EGADS : 5 0 Yes 3 1 1 2 5
EGADS : 6 0 Yes 4 2 1 2 3
EGADS : 7 0 Yes 1 5 1 4 5
EGADS : 8 0 Yes 3 6 1 4 5
EGADS : 9 0 Yes 5 6 1 4 6
EGADS : 10 0 Yes 6 5 1 5 6
EGADS : 11 1 Yes 8 7 NA 7 9
EGADS : 12 1 Yes 7 9 NA 7 12
EGADS : 13 1 Yes 10 9 NA 7 10
EGADS : 14 1 Yes 8 10 NA 7 11
EGADS : 15 1 Yes 12 11 NA 8 9
EGADS : 16 1 Yes 11 13 NA 8 12
EGADS : 17 1 Yes 14 13 NA 8 10
EGADS : 18 1 Yes 12 14 NA 8 11
EGADS : 19 1 Yes 8 12 NA 9 11
EGADS : 20 1 Yes 7 11 NA 9 12
EGADS : 21 1 Yes 10 14 NA 10 11
EGADS : 22 1 Yes 9 13 NA 10 12
EGADS : Node Information
EGADS : Node Active Coordinates
EGADS : 1 Yes 1.61374306 0 0
EGADS : 2 Yes 2.37421202 0 0.355213563
EGADS : 3 Yes 0 0 0
EGADS : 4 Yes 1.40965066 0 0.270825378
EGADS : 5 Yes 2.37421202 3.87298335 0.355213563
EGADS : 6 Yes 1.40965066 3.87298335 0.270825378
EGADS : 7 Yes 0 0 77.6430368
EGADS : 8 Yes 0 0 0
EGADS : 9 Yes 0 77.4596689 77.6430368
EGADS : 10 Yes 0 77.4596689 0
EGADS : 11 Yes 78.6462641 0 77.6430368
EGADS : 12 Yes 78.6462641 0 0
EGADS : 13 Yes 78.6462641 77.4596689 77.6430368
EGADS : 14 Yes 78.6462641 77.4596689 0
AFLR4 : Surface Mesh Spacing Setup
AFLR4 : Max Bounding Box Length = 154.919
AFLR4 : Min Bounding Box Length = 154.919
AFLR4 : Max Ref Bounding Box Length = 7.74597
AFLR4 : Min Ref Bounding Box Length = 0.433058
AFLR4 : Reference Length = 6.45497
AFLR4 : BL Thickness = 0
AFLR4 : FarField Spacing = 21.0478
AFLR4 : Abs Min Surf Spacing = 0.0161374
AFLR4 : Min Surf Spacing = 0.0322749
AFLR4 : Max Surf Spacing = 0.645497
AFLR4 : Global Scale Factor = 1
AFLR4 : Geometry Definition Information
AFLR4 : Definition Definition Composite Grid BC
AFLR4 : ID Type ID Type
AFLR4 : 0 glue-only composite - -
AFLR4 : 1 CAD geometry 0 STD w/BL
AFLR4 : 2 CAD geometry 0 STD w/BL
AFLR4 : 3 CAD geometry 0 STD w/BL
AFLR4 : 4 CAD geometry 0 STD w/BL
AFLR4 : 5 CAD geometry 0 STD w/BL
AFLR4 : 6 CAD geometry 0 STD w/BL
AFLR4 : 7 CAD geometry 0 FARFIELD
AFLR4 : 8 CAD geometry 0 FARFIELD
AFLR4 : 9 CAD geometry 0 FARFIELD
AFLR4 : 10 CAD geometry 0 FARFIELD
AFLR4 : 11 CAD geometry 0 FARFIELD
AFLR4 : 12 CAD geometry 0 FARFIELD
AFLR4 : Define CAD surface definition 1
AFLR4 : Define CAD surface definition 2
AFLR4 : Define CAD surface definition 3
AFLR4 : Define CAD surface definition 4
AFLR4 : Define CAD surface definition 5
AFLR4 : Define CAD surface definition 6
AFLR4 : Define CAD surface definition 7
AFLR4 : Define CAD surface definition 8
AFLR4 : Define CAD surface definition 9
AFLR4 : Define CAD surface definition 10
AFLR4 : Define CAD surface definition 11
AFLR4 : Define CAD surface definition 12
AFLR4 : Surface Grid Generation
AFLR4 : Generate optimal mesh on surface definition 1
AFLR2 : Nodes, Trias,Quads= 1658 3135 0
AFLR4 : Nodes, Trias,Quads= 971 1761 0
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Trias,Quads= 1628 3077 0
AFLR4 : Nodes, Trias,Quads= 941 1703 0
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Trias,Quads= 48 65 0
AFLR4 : Nodes, Trias,Quads= 44 57 0
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Trias,Quads= 1668 3155 0
AFLR4 : Nodes, Trias,Quads= 986 1791 0
AFLR4 : Generate optimal mesh on surface definition 5
AFLR2 : Nodes, Trias,Quads= 1625 3071 0
AFLR4 : Nodes, Trias,Quads= 930 1681 0
AFLR4 : Generate optimal mesh on surface definition 6
AFLR2 : Nodes, Trias,Quads= 48 65 0
AFLR4 : Nodes, Trias,Quads= 44 57 0
AFLR4 : Generate optimal mesh on surface definition 7
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 8
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 9
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 10
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 11
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 12
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes,Faces,BEdges= 3847 7686 938
AFLR4 : Curvature BG Surface Grid Generation
AFLR4 : Nodes, Faces = 3847 7686
AFLR4 : Surface Grid Generation
AFLR4 : Generate optimal mesh on surface definition 1
AFLR2 : Nodes, Trias,Quads= 6118 11925 0
AFLR4 : Nodes, Trias,Quads= 2408 4505 0
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Trias,Quads= 5960 11610 0
AFLR4 : Nodes, Trias,Quads= 2296 4282 0
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Trias,Quads= 147 230 0
AFLR4 : Nodes, Trias,Quads= 131 198 0
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Trias,Quads= 6173 12035 0
AFLR4 : Nodes, Trias,Quads= 2395 4479 0
AFLR4 : Generate optimal mesh on surface definition 5
AFLR2 : Nodes, Trias,Quads= 6053 11796 0
AFLR4 : Nodes, Trias,Quads= 2292 4274 0
AFLR4 : Generate optimal mesh on surface definition 6
AFLR2 : Nodes, Trias,Quads= 147 230 0
AFLR4 : Nodes, Trias,Quads= 131 198 0
AFLR4 : Generate optimal mesh on surface definition 7
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 8
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 9
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 10
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 11
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
AFLR4 : Generate optimal mesh on surface definition 12
AFLR2 : Nodes, Trias,Quads= 73 116 0
AFLR4 : Nodes, Trias,Quads= 68 106 0
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes,Faces,BEdges= 9290 18572 1526
OVERALL : CPU Time = 0.582 seconds
Body 1 (of 2)
Number of nodes = 8970
Number of elements = 17936
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 17936
Number of quadrilateral elements = 0
Body 2 (of 2)
Number of nodes = 320
Number of elements = 636
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 636
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 9290
Total number of elements = 18572
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = leftWing, index = 1
Name = riteWing, index = 2
Name = Farfield, index = 3
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Wing, index = 1
Name = Farfield, index = 2
Getting volume mesh
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.6
AFLR2 : Version Date 11/20/22 @ 09:21PM
AFLR2 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR2 : Compile Date 02/08/23 @ 12:48PM
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 11.3.17
AFLR4 : Version Date 03/03/23 @ 03:12PM
AFLR4 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR4 : Compile Date 03/03/23 @ 11:35PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.23
EGADS : OpenCASCADE Version 7.4.1
EGADS : ---------------------------------------
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes,Faces,BEdges= 9290 18572 1526
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
UG PARAM : mrecm = 3
UG PARAM : mrecqm = 3
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
UG PARAM : mrecm = 3
UG PARAM : mrecqm = 3
UG PARAM : mpfrmt = 0
AFLR3 : ---------------------------------------
AFLR3 : AFLR3 LIBRARY
AFLR3 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR3 : TETRAHEDRAL GRID GENERATOR
AFLR3 : Version Number 16.32.38
AFLR3 : Version Date 03/03/23 @ 03:11PM
AFLR3 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR3 : Compile Date 03/03/23 @ 11:34PM
AFLR3 : Copyright 1994-2021, D.L. Marcum
AFLR3 : ---------------------------------------
AFLR3 IC : INPUT SURFACE GRID CHECK
AFLR3 IC : Nodes, Elements = 9290 0
UG3 : Boundary Conditions
UG3 : B-Face ID Boundary Condition
UG3 : 1 Solid
UG3 : 2 Solid
UG3 : 3 Solid
UG3 : 4 Solid
UG3 : 5 Solid
UG3 : 6 Solid
UG3 : 7 FarField
UG3 : 8 FarField
UG3 : 9 FarField
UG3 : 10 FarField
UG3 : 11 FarField
UG3 : 12 FarField
AFLR3 : CPU Time = 0.020 seconds
AFLR3 IG : INITIAL VOLUME GRID GENERATION
AFLR3 IG : Nodes, Elements = 9290 0
AFLR3 IG : Nodes, Elements = 8 10
AFLR3 IG : Nodes, Elements = 1860 12646
AFLR3 IG : Nodes, Elements = 3720 25971
AFLR3 IG : Nodes, Elements = 5580 39697
AFLR3 IG : Nodes, Elements = 7440 54213
AFLR3 IG : Nodes, Elements = 9297 69672
AFLR3 IG : Nodes, Elements = 9297 69492
AFLR3 IG : Nodes, Elements = 9290 42442
AFLR3 IG : Nodes, Elements = 9290 42501
AFLR3 IG : Nodes, Elements = 9290 30785
AFLR3 IG : Nodes, Elements = 9290 28628
AFLR3 : CPU Time = 0.265 seconds
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
AFLR3 GG : Nodes, Elements = 9290 28628
AFLR3 GG : Nodes, Elements = 13561 41513
AFLR3 GG : Nodes, Elements = 13561 58358
AFLR3 GG : Nodes, Elements = 13561 53657
AFLR3 GG : Nodes, Elements = 17117 64735
AFLR3 GG : Nodes, Elements = 17117 78808
AFLR3 GG : Nodes, Elements = 17117 74279
AFLR3 GG : Nodes, Elements = 20675 85292
AFLR3 GG : Nodes, Elements = 20675 99081
AFLR3 GG : Nodes, Elements = 20675 94981
AFLR3 GG : Nodes, Elements = 24337 106153
AFLR3 GG : Nodes, Elements = 24337 120869
AFLR3 GG : Nodes, Elements = 24337 116773
AFLR3 GG : Nodes, Elements = 28106 128236
AFLR3 GG : Nodes, Elements = 28106 142965
AFLR3 GG : Nodes, Elements = 28106 139010
AFLR3 GG : Nodes, Elements = 31766 150079
AFLR3 GG : Nodes, Elements = 31766 164489
AFLR3 GG : Nodes, Elements = 31766 160588
AFLR3 GG : Nodes, Elements = 35380 171500
AFLR3 GG : Nodes, Elements = 35380 185811
AFLR3 GG : Nodes, Elements = 35380 182124
AFLR3 GG : Nodes, Elements = 38823 192508
AFLR3 GG : Nodes, Elements = 38823 206006
AFLR3 GG : Nodes, Elements = 38823 202470
AFLR3 GG : Nodes, Elements = 42134 212447
AFLR3 GG : Nodes, Elements = 42134 225390
AFLR3 GG : Nodes, Elements = 42134 222178
AFLR3 GG : Nodes, Elements = 45345 231848
AFLR3 GG : Nodes, Elements = 45345 244494
AFLR3 GG : Nodes, Elements = 45345 241207
AFLR3 GG : Nodes, Elements = 48398 250392
AFLR3 GG : Nodes, Elements = 48398 262281
AFLR3 GG : Nodes, Elements = 48398 259327
AFLR3 GG : Nodes, Elements = 51273 267969
AFLR3 GG : Nodes, Elements = 51273 279340
AFLR3 GG : Nodes, Elements = 51273 276462
AFLR3 GG : Nodes, Elements = 54042 284789
AFLR3 GG : Nodes, Elements = 54042 295506
AFLR3 GG : Nodes, Elements = 54042 292883
AFLR3 GG : Nodes, Elements = 56636 300683
AFLR3 GG : Nodes, Elements = 56636 310952
AFLR3 GG : Nodes, Elements = 56636 308342
AFLR3 GG : Nodes, Elements = 59123 315811
AFLR3 GG : Nodes, Elements = 59123 325722
AFLR3 GG : Nodes, Elements = 59123 323181
AFLR3 GG : Nodes, Elements = 61483 330272
AFLR3 GG : Nodes, Elements = 61483 339606
AFLR3 GG : Nodes, Elements = 61483 337245
AFLR3 GG : Nodes, Elements = 63678 343841
AFLR3 GG : Nodes, Elements = 63678 352418
AFLR3 GG : Nodes, Elements = 63678 350277
AFLR3 GG : Nodes, Elements = 65758 356528
AFLR3 GG : Nodes, Elements = 65758 364558
AFLR3 GG : Nodes, Elements = 65758 362578
AFLR3 GG : Nodes, Elements = 67790 368681
AFLR3 GG : Nodes, Elements = 67790 376603
AFLR3 GG : Nodes, Elements = 67790 374718
AFLR3 GG : Nodes, Elements = 69606 380169
AFLR3 GG : Nodes, Elements = 69606 387298
AFLR3 GG : Nodes, Elements = 69606 385523
AFLR3 GG : Nodes, Elements = 71286 390568
AFLR3 GG : Nodes, Elements = 71286 397091
AFLR3 GG : Nodes, Elements = 71286 395493
AFLR3 GG : Nodes, Elements = 72871 400253
AFLR3 GG : Nodes, Elements = 72871 406495
AFLR3 GG : Nodes, Elements = 72871 404928
AFLR3 GG : Nodes, Elements = 74289 409183
AFLR3 GG : Nodes, Elements = 74289 414668
AFLR3 GG : Nodes, Elements = 74289 413342
AFLR3 GG : Nodes, Elements = 75656 417447
AFLR3 GG : Nodes, Elements = 75656 422806
AFLR3 GG : Nodes, Elements = 75656 421489
AFLR3 GG : Nodes, Elements = 76889 425188
AFLR3 GG : Nodes, Elements = 76889 430052
AFLR3 GG : Nodes, Elements = 76889 428849
AFLR3 GG : Nodes, Elements = 78048 432330
AFLR3 GG : Nodes, Elements = 78048 436850
AFLR3 GG : Nodes, Elements = 78048 435708
AFLR3 GG : Nodes, Elements = 79141 438988
AFLR3 GG : Nodes, Elements = 79141 443321
AFLR3 GG : Nodes, Elements = 79141 442273
AFLR3 GG : Nodes, Elements = 80177 445384
AFLR3 GG : Nodes, Elements = 80177 449363
AFLR3 GG : Nodes, Elements = 80177 448421
AFLR3 GG : Nodes, Elements = 81132 451286
AFLR3 GG : Nodes, Elements = 81132 455027
AFLR3 GG : Nodes, Elements = 81132 454114
AFLR3 GG : Nodes, Elements = 81965 456616
AFLR3 GG : Nodes, Elements = 81965 459966
AFLR3 GG : Nodes, Elements = 81965 459099
AFLR3 GG : Nodes, Elements = 82658 461179
AFLR3 GG : Nodes, Elements = 82658 463902
AFLR3 GG : Nodes, Elements = 82658 463198
AFLR3 GG : Nodes, Elements = 83226 464902
AFLR3 GG : Nodes, Elements = 83226 467218
AFLR3 GG : Nodes, Elements = 83226 466581
AFLR3 GG : Nodes, Elements = 83659 467880
AFLR3 GG : Nodes, Elements = 83659 469692
AFLR3 GG : Nodes, Elements = 83659 469158
AFLR3 GG : Nodes, Elements = 83947 470023
AFLR3 GG : Nodes, Elements = 83947 471204
AFLR3 GG : Nodes, Elements = 83947 470847
AFLR3 GG : Nodes, Elements = 84133 471405
AFLR3 GG : Nodes, Elements = 84133 472156
AFLR3 GG : Nodes, Elements = 84133 471928
AFLR3 GG : Nodes, Elements = 84231 472222
AFLR3 GG : Nodes, Elements = 84231 472634
AFLR3 GG : Nodes, Elements = 84231 472491
AFLR3 GG : Nodes, Elements = 84273 472617
AFLR3 GG : Nodes, Elements = 84273 472798
AFLR3 GG : Nodes, Elements = 84273 472740
AFLR3 GG : Nodes, Elements = 84281 472764
AFLR3 GG : Nodes, Elements = 84281 472792
AFLR3 GG : Nodes, Elements = 84281 472781
AFLR3 GG : Nodes, Elements = 84287 472799
AFLR3 GG : Nodes, Elements = 84287 472813
AFLR3 GG : Nodes, Elements = 84287 472807
AFLR3 : CPU Time = 5.144 seconds
AFLR3 QI : QUALITY IMPROVEMENT
AFLR3 QI : Nodes, Elements = 84287 472807
AFLR3 QI : Nodes, Elements = 83845 470306
AFLR3 QI : Nodes, Elements = 83783 469957
AFLR3 QI : Nodes, Elements = 83774 469906
AFLR3 QI : Nodes, Elements = 83774 471765
AFLR3 QI : Nodes, Elements = 83774 469695
AFLR3 QI : Nodes, Elements = 83774 468779
AFLR3 QI : Nodes, Elements = 83774 469030
AFLR3 QI : Nodes, Elements = 83774 468600
AFLR3 QI : Nodes, Elements = 83774 468491
AFLR3 QI : Nodes, Elements = 83774 468696
AFLR3 QI : Nodes, Elements = 83774 468475
AFLR3 QI : Nodes, Elements = 83774 468435
AFLR3 QI : Nodes, Elements = 83774 468615
AFLR3 QI : Nodes, Elements = 83774 468429
AFLR3 QI : Nodes, Elements = 83774 468397
AFLR3 QI : Nodes, Elements = 83774 468606
AFLR3 QI : Nodes, Elements = 83774 468421
AFLR3 QI : Nodes, Elements = 83774 468402
AFLR3 QI : Nodes, Elements = 83775 468406
AFLR3 QI : Nodes, Elements = 83775 468587
AFLR3 QI : Nodes, Elements = 83775 468408
AFLR3 QI : Nodes, Elements = 83775 468401
AFLR3 QI : Nodes, Elements = 83775 468610
AFLR3 QI : Nodes, Elements = 83775 468402
AFLR3 QI : Nodes, Elements = 83775 468381
AFLR3 : CPU Time = 3.131 seconds
AFLR3 : DONE
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 468381
UG3 : Min, Max Ang = 13.82 158.3
UG3 : Average Angle = 70.2
UG3 : No. Angle>160.0 = 0
UG3 : No. Angle>179.9 = 0
UG3 : VOL CHECK
UG3 : Total-Volume = 3.72e+06
UG3 : No. Tet Elems = 468381
UG3 : Min Vol = 8.95e-07
UG3 : Average Vol = 7.94
UG3 : Total-Tet-Vol = 3.72e+06
UG3 : No. Vol<TOL = 0
UG3 : Q VOL-LENGTH-RATIO CHECK
2/3 2
UG3 : Q = c * Vol / sum( L )
UG3 : 0 <= Q <= 1
UG3 : No. Tet Elems = 468381
UG3 : Min, Max Q = 0.26 1
UG3 : Average Q = 0.902
UG3 : No. Q< 0.1 = 0
UG3 : No. Q< 0.01 = 0
OVERALL : CPU Time = 8.979 seconds
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 468381
UG3 : Min, Max Ang = 13.82 158.3
UG3 : Average Angle = 70.2
UG3 : No. Angle>160.0 = 0
UG3 : No. Angle>179.9 = 0
UG3 : VOL CHECK
UG3 : Total-Volume = 3.72e+06
UG3 : No. Tet Elems = 468381
UG3 : Min Vol = 8.95e-07
UG3 : Average Vol = 7.94
UG3 : Total-Tet-Vol = 3.72e+06
UG3 : No. Vol<TOL = 0
UG3 : Q VOL-LENGTH-RATIO CHECK
2/3 2
UG3 : Q = c * Vol / sum( L )
UG3 : 0 <= Q <= 1
UG3 : Note that L includes scaling for BL-aspect=ratio
UG3 : No. Tet Elems = 468381
UG3 : Min, Max Q = 0.383 1
UG3 : Average Q = 0.874
UG3 : No. Q< 0.1 = 0
UG3 : No. Q< 0.01 = 0
UG3 : CPU Time = 0.000 seconds
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.23
EGADS : OpenCASCADE Version 7.4.1
EGADS : ---------------------------------------
EGADS : CREATE EGADS TESS FROM AFLR3 DATA
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 1
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 2
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 3
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 4
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 5
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 6
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 7
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 8
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 9
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 10
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 1
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 2
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 3
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 4
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 5
EGADS : CREATING TESSELLATION FOR BODY 0 FACE 6
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 11
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 12
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 13
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 14
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 15
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 16
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 17
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 18
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 19
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 20
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 21
EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 22
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 7
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 8
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 9
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 10
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 11
EGADS : CREATING TESSELLATION FOR BODY 1 FACE 12
EGADS : EGADS TESS CREATED
EGADS : CHECK TESS GLOBAL FACE NODE MAP
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 1
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 2
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 3
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 4
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 5
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 6
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 7
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 8
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 9
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 10
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 11
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 12
Volume mesh:
Number of nodes = 83775
Number of elements = 486953
Number of triangles = 18572
Number of quadrilatarals = 0
Number of tetrahedrals = 468381
Number of pyramids = 0
Number of prisms = 0
Number of hexahedrals = 0
No project name ("Proj_Name") provided - A volume mesh will not be written out
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wing
Done getting CFD boundary conditions
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2022, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 10 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 7.74597 m.
Reference origin for moment evaluation is (0.322749, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.
Surface(s) plotted in the output file: BC_1.
Surface(s) affected by the design variables: BC_1.
Input mesh file name: ../aflr3/aflr3_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|
| TECPLOT| 250|
| SURFACE_TECPLOT| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface file name: surface_flow_aeroelasticIterative.
Volume file name: flow_aeroelasticIterative.
Restart file name: restart_flow_aeroelasticIterative.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
83775 grid points.
468381 volume elements.
2 surface markers.
17936 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
468381 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: 3.71806e+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: 431.689. Mean K: 20.6394. Standard deviation K: 49.3925.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 47.2388| 86.636|
| CV Face Area Aspect Ratio| 1.07945| 107.626|
| CV Sub-Volume Ratio| 1| 835.999|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 83775| 1/1.00| 10|
| 1| 13821| 1/6.06| 8.22684|
| 2| 2125| 1/6.5| 6.61095|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5583 m^2.
Area projection in the x-plane = 1.53011 m^2, y-plane = 0.868549 m^2, z-plane = 9.83638 m^2.
Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399868 m.
Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0329598 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 211798| 1| m^2/s^2| 211798|
| Velocity-X| 100.087| 1| m/s| 100.087|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 0| 1| m/s| 0|
| Velocity Magnitude| 100.087| 1| m/s| 100.087|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 5.6935e+00| -1.769868| 0.448506| 0.049654| 3.699238| -0.549589|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.6131e+00| -1.514606| 0.839346| 0.462880| 3.962010| -0.289362|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.3677e+00| -1.526763| 0.926179| 0.740347| 3.939565| 1.925842|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 5.2183e+00| -1.606192| 0.945796| 0.806951| 3.854348| -8.538088|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 5.1595e+00| -1.480946| 0.895276| 0.699471| 3.988747| -5.572881|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.48095| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticIterative.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|CSV file |surface_flow_aeroelasticIterative.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary |flow_aeroelasticIterative.szplt |
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary surface |surface_flow_aeroelasticIterative.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
==> Running SU2 post-analysis...
==> Running ASTROS pre-analysis...
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 265
Number of elements = 346
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 346
----------------------------
Total number of nodes = 265
Total number of elements = 346
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 265
Number of elements = 346
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 346
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 1
Load name - pressureAero
No "groupName" specified for Load tuple pressureAero, going to use load name
Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
CAPS Info: Reparameterization Bound -> upperWing -- nu, nv = 129 129
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 8970
CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.249086e+09, tgt = 6.249086e+09, diff = 2.904410e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 8970
CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.101315e+09, tgt = 6.101315e+09, diff = 1.479870e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 8970
CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.122063e+07, tgt = 6.122063e+07, diff = 7.450581e-09
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 8970
CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.122314e+07, tgt = 6.122314e+07, diff = 0.000000e+00
Extracting external pressure loads from data transfer....
TransferName = upperWing
Number of Elements = 96 (total = 96)
TransferName = lowerWing
Number of Elements = 96 (total = 192)
TransferName = leftTip
Number of Elements = 10 (total = 202)
TransferName = riteTip
Number of Elements = 10 (total = 212)
Writing Astros grid and connectivity file (in free field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
Running mASTROS......
==> Running ASTROS post-analysis...
==> Running SU2 pre-analysis...
Writing boundary flags
- bcProps.surfaceProp[0].surfaceType = 3
- bcProps.surfaceProp[1].surfaceType = 1
Done boundary flags
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Mesh Deformation Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../aflr3/aflr3_0.su2
---------------- Grid deformation parameters ( Zone 0 ) ----------------
Grid deformation using a linear elasticity method.
-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aeroelasticIterative.su2.
Cell stiffness scaled by distance to nearest solid surface.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| BC_2|
+-----------------------------------------------------------------------+
Three dimensional problem.
83775 grid points.
468381 volume elements.
2 surface markers.
17936 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
468381 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: 3.71806e+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
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).
----------------------- Write deformed grid files -----------------------
|SU2 mesh |aeroelasticIterative.su2 |
|CSV file |surface_deformed.csv |
|Tecplot binary |volume_deformed.szplt |
|Tecplot binary surface |surface_deformed.szplt |
Adding any FFD information to the SU2 file.
------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.
Completed in 24.888575 seconds on 1 core.
------------------------- Exit Success (SU2_DEF) ------------------------
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2022, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 10 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 7.74597 m.
Reference origin for moment evaluation is (0.322749, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.
Surface(s) plotted in the output file: BC_1.
Surface(s) affected by the design variables: BC_1.
Input mesh file name: ../aflr3/aflr3_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|
| TECPLOT| 250|
| SURFACE_TECPLOT| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface file name: surface_flow_aeroelasticIterative.
Volume file name: flow_aeroelasticIterative.
Restart file name: restart_flow_aeroelasticIterative.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
83775 grid points.
468381 volume elements.
2 surface markers.
17936 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
468381 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: 3.71806e+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: 431.689. Mean K: 20.6394. Standard deviation K: 49.3925.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 47.2388| 86.636|
| CV Face Area Aspect Ratio| 1.07945| 107.626|
| CV Sub-Volume Ratio| 1| 835.999|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 83775| 1/1.00| 10|
| 1| 13821| 1/6.06| 8.22684|
| 2| 2125| 1/6.5| 6.61095|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5583 m^2.
Area projection in the x-plane = 1.53011 m^2, y-plane = 0.868549 m^2, z-plane = 9.83638 m^2.
Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399868 m.
Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0329598 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 211798| 1| m^2/s^2| 211798|
| Velocity-X| 100.087| 1| m/s| 100.087|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 0| 1| m/s| 0|
| Velocity Magnitude| 100.087| 1| m/s| 100.087|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 3.1683e+00| -1.769868| 0.448506| 0.049654| 3.699238| -0.549589|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.0982e+00| -1.514606| 0.839346| 0.462880| 3.962010| -0.289362|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.1073e+00| -1.526763| 0.926179| 0.740347| 3.939565| 1.925842|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.2068e+00| -1.606192| 0.945796| 0.806951| 3.854348| -8.538088|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.4918e+00| -1.480946| 0.895276| 0.699471| 3.988747| -5.572881|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.48095| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticIterative.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|CSV file |surface_flow_aeroelasticIterative.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary |flow_aeroelasticIterative.szplt |
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary surface |surface_flow_aeroelasticIterative.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
==> Running SU2 post-analysis...
==> Running ASTROS pre-analysis...
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 8970
CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.249086e+09, tgt = 6.249086e+09, diff = 2.904410e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 8970
CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.101315e+09, tgt = 6.101315e+09, diff = 1.479870e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 8970
CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.122063e+07, tgt = 6.122063e+07, diff = 7.450581e-09
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 8970
CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.122314e+07, tgt = 6.122314e+07, diff = 0.000000e+00
Extracting external pressure loads from data transfer....
TransferName = upperWing
Number of Elements = 96 (total = 96)
TransferName = lowerWing
Number of Elements = 96 (total = 192)
TransferName = leftTip
Number of Elements = 10 (total = 202)
TransferName = riteTip
Number of Elements = 10 (total = 212)
Writing Astros grid and connectivity file (in free field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
Running mASTROS......
==> Running ASTROS post-analysis...
real 3m26.844s
user 3m39.799s
sys 1m54.317s
+ status=0
+ set +x
=================================================
data/session11/aeroelastic_2_Iterative_SU2_Astros.py passed (as expected)
=================================================
*************************************************
*************************************************
=================================================
Did not run examples for:
session08 fun3d
session11 fun3d+astros
=================================================
=================================================
Summary of examples NOT finished as expected
data/session07/pointwise_01_Defaults.py
data/session07/pointwise_02_InviscidWing.py
data/session07/pointwise_03_TurnAngle.py
data/session07/pointwise_04_TurnAngleHard.py
data/session07/pointwise_05_DomainDecay.py
data/session07/pointwise_06_ConnectorProximity.py
data/session07/pointwise_07_InviscidTransport.py
data/session07/pointwise_08_ViscousWing.py
solutions/session07/pointwise_DomainProximity.py
See training.log for more details.
=================================================
Build step 'Execute shell' marked build as failure
[GNU C Compiler (gcc)Clang] Skipping execution of recorder since overall result is 'FAILURE'
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] Skipped based on build state FAILURE
Finished: FAILURE