| 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.
146129 grid points.
825319 volume elements.
2 surface markers.
25868 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
825319 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: 25.1238. Mean K: 1.30702. Standard deviation K: 3.04293.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 50.934| 86.73|
| CV Face Area Aspect Ratio| 1.02773| 131.994|
| CV Sub-Volume Ratio| 1.04037| 855.777|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 146129| 1/1.00| 10|
| 1| 23999| 1/6.09| 8.21442|
| 2| 3650| 1/6.58| 6.5771|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 97.6729 m.
Wetted area = 8684.95 m^2.
Area projection in the x-plane = 678.503 m^2, y-plane = 443.208 m^2, z-plane = 4163.51 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 = -5.479 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| 5.0296e+00| 0.936995| 3.213583| 2.934955| 6.419840| -0.377900|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.0053e+00| 1.006321| 3.498820| 3.145318| 6.507595| 0.088151|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 4.9364e+00| 1.079554| 3.620951| 3.393924| 6.570727| 1.643092|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 4.9032e+00| 1.159272| 3.739303| 3.531651| 6.646057| 7.067347|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 4.8863e+00| 1.220896| 3.827792| 3.616074| 6.713641| 37.425264|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 1.2209| < -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 = 0.322644 Cd = 0.008621
--> Cmx = -6.4e-05 Cmy = -0.052982 Cmz = 1.1e-05
--> Cx = 0.002989 Cy = -8.2e-05 Cz = 0.322745
real 0m55.283s
user 0m53.477s
sys 0m2.175s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
SELECT specified nonexistant Edge
--> catching signal -223 (edge_not_found)
real 0m59.232s
user 2m41.244s
sys 2m56.442s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 = 11092
Number of elements = 22807
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 22807
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 11092
Total number of elements = 22807
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 = 11921
Number of elements = 24465
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 24465
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 11921
Total number of elements = 24465
real 0m48.656s
user 2m42.594s
sys 2m59.661s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 = 732
Number of elements = 1781
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 1781
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 732
Total number of elements = 1781
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 = 934
Number of elements = 2228
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 2228
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 934
Total number of elements = 2228
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 = 3545
Number of elements = 7669
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 7669
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3545
Total number of elements = 7669
real 0m46.505s
user 2m38.440s
sys 2m55.269s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 = 1406
Number of elements = 3137
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 3137
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 1406
Total number of elements = 3137
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 = 2097
Number of elements = 4570
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 4570
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 2097
Total number of elements = 4570
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 = 6562
Number of elements = 13689
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 13689
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 6562
Total number of elements = 13689
real 0m48.788s
user 2m41.142s
sys 2m59.906s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 = 3538
Number of elements = 7417
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 7417
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3538
Total number of elements = 7417
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 = 12458
Number of elements = 25384
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 25384
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 12458
Total number of elements = 25384
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 = 45075
Number of elements = 90817
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 90817
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 45075
Total number of elements = 90817
real 0m51.550s
user 2m54.639s
sys 2m56.701s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 = 8302
Number of elements = 17191
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 17191
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 8302
Total number of elements = 17191
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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 = 1655
Number of elements = 3225
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 3225
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 1655
Total number of elements = 3225
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 1m19.554s
user 3m14.094s
sys 2m56.043s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 = 8302
Number of elements = 17191
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 17191
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 8302
Total number of elements = 17191
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 = 3919
Number of elements = 8410
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 8410
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3919
Total number of elements = 8410
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 0m49.297s
user 2m40.856s
sys 2m49.711s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 = 1655
Number of elements = 3225
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 3225
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 1655
Total number of elements = 3225
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 = 6587
Number of elements = 13200
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 13200
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 6587
Total number of elements = 13200
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 = 22190
Number of elements = 22191
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 22191
----------------------------
Total number of nodes = 22190
Total number of elements = 22191
real 0m54.153s
user 2m41.160s
sys 2m52.469s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 0m44.230s
user 2m26.886s
sys 3m4.041s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 0m49.109s
user 2m32.873s
sys 2m46.764s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 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
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
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 = 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 : 0.0357647
2 : 0.102451
3 : 0.102451
4 : 0.159637
5 : 0.159637
6 : 0.215446
7 : 0.215446
8 : 0.350115
9 : 0.350115
10: 0.466966
real 0m49.181s
user 2m33.106s
sys 2m53.133s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 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
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
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 : 0.0357647
2 : 0.0533161
3 : 0.102451
4 : 0.102496
5 : 0.159637
6 : 0.211734
7 : 0.215446
8 : 0.223928
9 : 0.350115
10: 0.432754
real 0m48.138s
user 2m30.419s
sys 2m55.157s
+ 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/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 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
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
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 43461.879162311016
--> T1max 738.595
--> T2max 3686.25
--> T3max 43363.8
real 0m49.908s
user 2m31.660s
sys 2m46.219s
+ status=0
+ set +x
=================================================
data/session10/astros_3_StaticClamped.py passed (as expected)
=================================================
=================================================
astros_4_Composite.py test;
+ python astros_4_Composite.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/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_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 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
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
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 0m48.356s
user 2m31.028s
sys 2m58.002s
+ 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/7.6/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...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/jenkins/workspace/ESP_UndefinedCaps/7.6/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 = 7
Name = Wing, index = 1
Name = wingSpar2, index = 2
Name = wingRib, index = 3
Name = riteWingSkin, index = 4
Name = wingSpar1, index = 5
Name = leftWingSkin, index = 6
Name = wingTE, index = 7
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
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Body 1 (of 4)
Number of nodes = 7
Number of elements = 3
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 3
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Body 2 (of 4)
Number of nodes = 7
Number of elements = 3
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 3
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Body 3 (of 4)
Number of nodes = 7
Number of elements = 3
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 3
Body 4 (of 4)
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 = 320
Total number of elements = 396
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 capsGroup attributes ................
Number of unique capsGroup attributes = 7
Name = Wing, index = 1
Name = wingSpar2, index = 2
Name = wingRib, index = 3
Name = riteWingSkin, index = 4
Name = wingSpar1, index = 5
Name = leftWingSkin, index = 6
Name = wingTE, index = 7
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 7
Number of elements = 3
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 3
Setting FEA Data
Mesh for body = 1
Number of nodal coordinates = 7
Number of elements = 3
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 3
Setting FEA Data
Mesh for body = 2
Number of nodal coordinates = 7
Number of elements = 3
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 3
Setting FEA Data
Mesh for body = 3
Number of nodal coordinates = 299
Number of elements = 387
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 387
Combining multiple FEA meshes!
Combined Number of nodal coordinates = 320
Combined Number of elements = 396
Combined Elemental Nodes = 0
Combined Elemental Rods = 0
Combined Elemental Tria3 = 0
Combined Elemental Quad4 = 396
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 = 12
Surface 2: Number of points found for aero-spline = 12
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 0m51.125s
user 2m44.632s
sys 3m34.353s
+ 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/7.6/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 9.14.3
AFLR2 : Version Date 06/09/22 @ 05:16PM
AFLR2 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR2 : Compile Date 06/13/22 @ 12:42PM
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 10.22.23
AFLR4 : Version Date 07/14/22 @ 02:23PM
AFLR4 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR4 : Compile Date 07/19/22 @ 12:23AM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.22
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
EGADS : EGADS CAD Geometry Setup
EGADS : Model has 2 Active Bodies
EGADS : Body 0 is a SolidBody
EGADS : Body 0 has 1 Shells
EGADS : Body 0 has 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 : 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 IER ER Scale Neighbor
EGADS : ID Active ID Flag Weight Factor Faces
EGADS : 1 Yes 0 1 1 1 2 3 4
EGADS : 2 Yes 0 1 1 1 1 3 5
EGADS : 3 Yes 0 1 1 1 1 2
EGADS : 4 Yes 0 1 1 1 1 5 6
EGADS : 5 Yes 0 1 1 1 2 4 6
EGADS : 6 Yes 0 1 1 1 4 5
EGADS : 7 Yes 1 1 NA NA 9 10 11 12
EGADS : 8 Yes 1 1 NA NA 9 10 11 12
EGADS : 9 Yes 1 1 NA NA 7 8 11 12
EGADS : 10 Yes 1 1 NA NA 7 8 11 12
EGADS : 11 Yes 1 1 NA NA 7 8 9 10
EGADS : 12 Yes 1 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, Faces = 1658 3135
AFLR4 : Nodes, Faces = 983 1785
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Faces = 1628 3077
AFLR4 : Nodes, Faces = 934 1689
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Faces = 48 65
AFLR4 : Nodes, Faces = 44 57
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Faces = 1668 3155
AFLR4 : Nodes, Faces = 974 1767
AFLR4 : Generate optimal mesh on surface definition 5
AFLR2 : Nodes, Faces = 1625 3071
AFLR4 : Nodes, Faces = 918 1657
AFLR4 : Generate optimal mesh on surface definition 6
AFLR2 : Nodes, Faces = 48 65
AFLR4 : Nodes, Faces = 44 57
AFLR4 : Generate optimal mesh on surface definition 7
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 8
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 9
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 10
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 11
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 12
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes,Faces,BEdges= 3828 7648 938
AFLR4 : Curvature BG Surface Grid Generation
AFLR4 : Nodes, Faces = 3828 7648
AFLR4 : Surface Grid Generation
AFLR4 : Generate optimal mesh on surface definition 1
AFLR2 : Nodes, Faces = 3391 6471
AFLR4 : Nodes, Faces = 2424 4537
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Faces = 3389 6468
AFLR4 : Nodes, Faces = 2255 4200
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Faces = 145 226
AFLR4 : Nodes, Faces = 137 210
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Faces = 3360 6409
AFLR4 : Nodes, Faces = 2432 4553
AFLR4 : Generate optimal mesh on surface definition 5
AFLR2 : Nodes, Faces = 3367 6424
AFLR4 : Nodes, Faces = 2298 4286
AFLR4 : Generate optimal mesh on surface definition 6
AFLR2 : Nodes, Faces = 145 226
AFLR4 : Nodes, Faces = 137 210
AFLR4 : Generate optimal mesh on surface definition 7
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 8
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 9
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 10
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 11
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
AFLR4 : Generate optimal mesh on surface definition 12
AFLR2 : Nodes, Faces = 73 116
AFLR4 : Nodes, Faces = 68 106
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes,Faces,BEdges= 9320 18632 1526
OVERALL : CPU Time = 0.606 seconds
Body 1 (of 2)
Number of nodes = 9000
Number of elements = 17996
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 17996
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 = 9320
Total number of elements = 18632
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
Number of surface nodes - 9320
Number of surface elements - 18632
Getting volume mesh
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.3
AFLR2 : Version Date 06/09/22 @ 05:16PM
AFLR2 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR2 : Compile Date 06/13/22 @ 12:42PM
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 10.22.23
AFLR4 : Version Date 07/14/22 @ 02:23PM
AFLR4 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR4 : Compile Date 07/19/22 @ 12:23AM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.22
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
OVERALL : CPU Time = 0.504 seconds
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes,Faces,BEdges= 9320 18632 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 16.32.32
AFLR3 : Version Date 06/10/22 @ 01:15PM
AFLR3 : Compile OS Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR3 : Compile Date 06/24/22 @ 03:12PM
AFLR3 : Copyright 1994-2021, D.L. Marcum
AFLR3 : ---------------------------------------
AFLR3 IC : INPUT SURFACE GRID CHECK
AFLR3 IC : Nodes, Elements = 9320 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 = 0.019 seconds
AFLR3 IG : INITIAL VOLUME GRID GENERATION
AFLR3 IG : Nodes, Elements = 9320 0
AFLR3 IG : Nodes, Elements = 8 10
AFLR3 IG : Nodes, Elements = 1866 12712
AFLR3 IG : Nodes, Elements = 3732 26115
AFLR3 IG : Nodes, Elements = 5598 39852
AFLR3 IG : Nodes, Elements = 7464 54343
AFLR3 IG : Nodes, Elements = 9327 69980
AFLR3 IG : Nodes, Elements = 9327 69786
AFLR3 IG : Nodes, Elements = 9327 64954
AFLR3 IG : Nodes, Elements = 9327 63454
AFLR3 IG : Nodes, Elements = 9327 63453
AFLR3 IG : Nodes, Elements = 9320 36301
AFLR3 IG : Nodes, Elements = 9320 42408
AFLR3 IG : Nodes, Elements = 9320 30451
AFLR3 IG : Nodes, Elements = 9320 28149
AFLR3 : CPU Time = 0.318 seconds
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
AFLR3 GG : Nodes, Elements = 9320 28149
AFLR3 GG : Nodes, Elements = 13699 41351
AFLR3 GG : Nodes, Elements = 13699 58816
AFLR3 GG : Nodes, Elements = 13699 54352
AFLR3 GG : Nodes, Elements = 17428 65921
AFLR3 GG : Nodes, Elements = 17428 80425
AFLR3 GG : Nodes, Elements = 17428 75760
AFLR3 GG : Nodes, Elements = 20984 86777
AFLR3 GG : Nodes, Elements = 20984 100666
AFLR3 GG : Nodes, Elements = 20984 96611
AFLR3 GG : Nodes, Elements = 24684 107830
AFLR3 GG : Nodes, Elements = 24684 122340
AFLR3 GG : Nodes, Elements = 24684 118457
AFLR3 GG : Nodes, Elements = 28452 129886
AFLR3 GG : Nodes, Elements = 28452 144581
AFLR3 GG : Nodes, Elements = 28452 140704
AFLR3 GG : Nodes, Elements = 32050 151561
AFLR3 GG : Nodes, Elements = 32050 165780
AFLR3 GG : Nodes, Elements = 32050 162054
AFLR3 GG : Nodes, Elements = 35624 172813
AFLR3 GG : Nodes, Elements = 35624 186856
AFLR3 GG : Nodes, Elements = 35624 183277
AFLR3 GG : Nodes, Elements = 39078 193672
AFLR3 GG : Nodes, Elements = 39078 207271
AFLR3 GG : Nodes, Elements = 39078 203883
AFLR3 GG : Nodes, Elements = 42377 213821
AFLR3 GG : Nodes, Elements = 42377 226594
AFLR3 GG : Nodes, Elements = 42377 223445
AFLR3 GG : Nodes, Elements = 45504 232850
AFLR3 GG : Nodes, Elements = 45504 245050
AFLR3 GG : Nodes, Elements = 45504 242015
AFLR3 GG : Nodes, Elements = 48506 251047
AFLR3 GG : Nodes, Elements = 48506 262865
AFLR3 GG : Nodes, Elements = 48506 259891
AFLR3 GG : Nodes, Elements = 51402 268591
AFLR3 GG : Nodes, Elements = 51402 279793
AFLR3 GG : Nodes, Elements = 51402 277041
AFLR3 GG : Nodes, Elements = 54104 285156
AFLR3 GG : Nodes, Elements = 54104 295759
AFLR3 GG : Nodes, Elements = 54104 293091
AFLR3 GG : Nodes, Elements = 56634 300692
AFLR3 GG : Nodes, Elements = 56634 310694
AFLR3 GG : Nodes, Elements = 56634 308228
AFLR3 GG : Nodes, Elements = 59086 315602
AFLR3 GG : Nodes, Elements = 59086 325172
AFLR3 GG : Nodes, Elements = 59086 322785
AFLR3 GG : Nodes, Elements = 61398 329727
AFLR3 GG : Nodes, Elements = 61398 338809
AFLR3 GG : Nodes, Elements = 61398 336551
AFLR3 GG : Nodes, Elements = 63531 342957
AFLR3 GG : Nodes, Elements = 63531 351470
AFLR3 GG : Nodes, Elements = 63531 349292
AFLR3 GG : Nodes, Elements = 65523 355273
AFLR3 GG : Nodes, Elements = 65523 363113
AFLR3 GG : Nodes, Elements = 65523 361158
AFLR3 GG : Nodes, Elements = 67367 366696
AFLR3 GG : Nodes, Elements = 67367 373915
AFLR3 GG : Nodes, Elements = 67367 372123
AFLR3 GG : Nodes, Elements = 69121 377387
AFLR3 GG : Nodes, Elements = 69121 384191
AFLR3 GG : Nodes, Elements = 69121 382549
AFLR3 GG : Nodes, Elements = 70709 387318
AFLR3 GG : Nodes, Elements = 70709 393617
AFLR3 GG : Nodes, Elements = 70709 392034
AFLR3 GG : Nodes, Elements = 72154 396369
AFLR3 GG : Nodes, Elements = 72154 401986
AFLR3 GG : Nodes, Elements = 72154 400579
AFLR3 GG : Nodes, Elements = 73538 404732
AFLR3 GG : Nodes, Elements = 73538 410170
AFLR3 GG : Nodes, Elements = 73538 408845
AFLR3 GG : Nodes, Elements = 74833 412731
AFLR3 GG : Nodes, Elements = 74833 417772
AFLR3 GG : Nodes, Elements = 74833 416564
AFLR3 GG : Nodes, Elements = 76063 420258
AFLR3 GG : Nodes, Elements = 76063 424942
AFLR3 GG : Nodes, Elements = 76063 423841
AFLR3 GG : Nodes, Elements = 77160 427134
AFLR3 GG : Nodes, Elements = 77160 431404
AFLR3 GG : Nodes, Elements = 77160 430393
AFLR3 GG : Nodes, Elements = 78190 433484
AFLR3 GG : Nodes, Elements = 78190 437528
AFLR3 GG : Nodes, Elements = 78190 436519
AFLR3 GG : Nodes, Elements = 79146 439387
AFLR3 GG : Nodes, Elements = 79146 443095
AFLR3 GG : Nodes, Elements = 79146 442217
AFLR3 GG : Nodes, Elements = 79942 444605
AFLR3 GG : Nodes, Elements = 79942 447702
AFLR3 GG : Nodes, Elements = 79942 446960
AFLR3 GG : Nodes, Elements = 80589 448902
AFLR3 GG : Nodes, Elements = 80589 451545
AFLR3 GG : Nodes, Elements = 80589 450824
AFLR3 GG : Nodes, Elements = 81070 452268
AFLR3 GG : Nodes, Elements = 81070 454232
AFLR3 GG : Nodes, Elements = 81070 453700
AFLR3 GG : Nodes, Elements = 81370 454602
AFLR3 GG : Nodes, Elements = 81370 455894
AFLR3 GG : Nodes, Elements = 81370 455489
AFLR3 GG : Nodes, Elements = 81531 455973
AFLR3 GG : Nodes, Elements = 81531 456671
AFLR3 GG : Nodes, Elements = 81531 456439
AFLR3 GG : Nodes, Elements = 81590 456616
AFLR3 GG : Nodes, Elements = 81590 456885
AFLR3 GG : Nodes, Elements = 81590 456779
AFLR3 GG : Nodes, Elements = 81613 456848
AFLR3 GG : Nodes, Elements = 81613 456938
AFLR3 GG : Nodes, Elements = 81613 456906
AFLR3 GG : Nodes, Elements = 81617 456918
AFLR3 GG : Nodes, Elements = 81617 456940
AFLR3 GG : Nodes, Elements = 81617 456931
AFLR3 GG : Nodes, Elements = 81619 456937
AFLR3 GG : Nodes, Elements = 81619 456942
AFLR3 GG : Nodes, Elements = 81619 456941
AFLR3 GG : Nodes, Elements = 81622 456950
AFLR3 GG : Nodes, Elements = 81622 456966
AFLR3 GG : Nodes, Elements = 81622 456955
AFLR3 : CPU Time = 3.638 seconds
AFLR3 QI : QUALITY IMPROVEMENT
AFLR3 QI : Nodes, Elements = 81622 456955
AFLR3 QI : Nodes, Elements = 81261 454894
AFLR3 QI : Nodes, Elements = 81217 454646
AFLR3 QI : Nodes, Elements = 81211 454613
AFLR3 QI : Nodes, Elements = 81210 454607
AFLR3 QI : Nodes, Elements = 81210 456522
AFLR3 QI : Nodes, Elements = 81210 454482
AFLR3 QI : Nodes, Elements = 81210 453617
AFLR3 QI : Nodes, Elements = 81210 455109
AFLR3 QI : Nodes, Elements = 81210 453586
AFLR3 QI : Nodes, Elements = 81210 453541
AFLR3 QI : Nodes, Elements = 81210 454958
AFLR3 QI : Nodes, Elements = 81210 453566
AFLR3 QI : Nodes, Elements = 81210 453541
AFLR3 QI : Nodes, Elements = 81210 454925
AFLR3 QI : Nodes, Elements = 81210 453553
AFLR3 QI : Nodes, Elements = 81210 453531
AFLR3 QI : Nodes, Elements = 81210 454909
AFLR3 QI : Nodes, Elements = 81210 453548
AFLR3 QI : Nodes, Elements = 81210 453527
AFLR3 QI : Nodes, Elements = 81211 453531
AFLR3 QI : Nodes, Elements = 81211 454906
AFLR3 QI : Nodes, Elements = 81211 453550
AFLR3 QI : Nodes, Elements = 81211 453534
AFLR3 QI : Nodes, Elements = 81211 454897
AFLR3 QI : Nodes, Elements = 81211 453544
AFLR3 QI : Nodes, Elements = 81211 453531
AFLR3 : CPU Time = 2.045 seconds
AFLR3 QRG: QUALITY GRID RE-GENERATION
AFLR3 QRG: Nodes, Elements = 81211 453531
AFLR3 QRG: Nodes, Elements = 81212 453532
AFLR3 : CPU Time = 0.056 seconds
AFLR3 : DONE
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 453532
UG3 : Min, Max Ang = 8.048 164
UG3 : Average Angle = 70.2
UG3 : No. Angle>160.0 = 4
UG3 : No. Angle>179.9 = 0
UG3 : VOL CHECK
UG3 : Total-Volume = 3.72e+06
UG3 : No. Tet Elems = 453532
UG3 : Min Vol = 1.11e-06
UG3 : Average Vol = 8.2
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 = 453532
UG3 : Min, Max Q = 0.123 1
UG3 : Average Q = 0.861
UG3 : No. Q< 0.1 = 0
UG3 : No. Q< 0.01 = 0
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 453532
UG3 : Min, Max Ang = 8.048 164
UG3 : Average Angle = 70.2
UG3 : No. Angle>160.0 = 4
UG3 : No. Angle>179.9 = 0
UG3 : VOL CHECK
UG3 : Total-Volume = 3.72e+06
UG3 : No. Tet Elems = 453532
UG3 : Min Vol = 1.11e-06
UG3 : Average Vol = 8.2
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 = 453532
UG3 : Min, Max Q = 0.24 1
UG3 : Average Q = 0.845
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 1.22
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
OVERALL : CPU Time = 0.335 seconds
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
UG_IO : OUTPUT GRID
UG_IO : Writing Data
UG_IO : Grid File Name = /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/session11/workDir_2_Aeroelastic_Iterative/Scratch/aflr3/aflr3_0.lb8.ugrid
UG_IO : Quad Surface Faces= 0
UG_IO : Tria Surface Faces= 18632
UG_IO : Quad Int. Faces = 0
UG_IO : Tria Int. Faces = 897748
UG_IO : Nodes = 81212
UG_IO : Total Elements = 453532
UG_IO : Hex Elements = 0
UG_IO : Pent_5 Elements = 0
UG_IO : Pent_6 Elements = 0
UG_IO : Tet Elements = 453532
UG_IO : CPU Time = 0.006 seconds
Volume mesh:
Number of nodes = 81212
Number of elements = 472164
Number of triangles = 18632
Number of quadrilatarals = 0
Number of tetrahedrals = 453532
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 (7.3.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.3.1 "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.
81212 grid points.
453532 volume elements.
2 surface markers.
17996 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
453532 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: 20.5059. Standard deviation K: 49.1995.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 49.1472| 85.0831|
| CV Face Area Aspect Ratio| 1.02671| 146.013|
| CV Sub-Volume Ratio| 1| 494.707|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 81212| 1/1.00| 10|
| 1| 13368| 1/6.08| 8.22066|
| 2| 2027| 1/6.59| 6.57547|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5565 m^2.
Area projection in the x-plane = 1.53007 m^2, y-plane = 0.868422 m^2, z-plane = 9.83485 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 = -0.0329185 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| 2.8353e+00| -1.764878| 0.454105| 0.056364| 3.704228| -0.551627|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.0579e+00| -1.601678| 0.768552| 0.497187| 3.871933| -0.295784|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.0917e+00| -1.630268| 0.891975| 0.713693| 3.838956| 1.702462|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.0731e+00| -1.744248| 0.878715| 0.743771| 3.718831| -8.900276|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.0014e+00| -1.696893| 0.776009| 0.664214| 3.767031| -5.371341|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.69689| < -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 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
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
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 = 9000
CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.247207e+09, tgt = 6.247207e+09, diff = 3.221403e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 9000
CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.100569e+09, tgt = 6.100569e+09, diff = 2.289438e-01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 9000
CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.124625e+07, tgt = 6.124625e+07, diff = 1.490116e-08
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 9000
CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.121854e+07, tgt = 6.121854e+07, diff = 7.450581e-09
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 large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
Running mASTROS......
==> Running 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 (7.3.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.3.1 "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.
81212 grid points.
453532 volume elements.
2 surface markers.
17996 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
453532 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 24.786154 seconds on 1 core.
------------------------- Exit Success (SU2_DEF) ------------------------
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.3.1 "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.
81212 grid points.
453532 volume elements.
2 surface markers.
17996 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
453532 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: 20.5059. Standard deviation K: 49.1995.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 49.1472| 85.0831|
| CV Face Area Aspect Ratio| 1.02671| 146.013|
| CV Sub-Volume Ratio| 1| 494.707|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 81212| 1/1.00| 10|
| 1| 13368| 1/6.08| 8.22066|
| 2| 2027| 1/6.59| 6.57547|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5565 m^2.
Area projection in the x-plane = 1.53007 m^2, y-plane = 0.868422 m^2, z-plane = 9.83485 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 = -0.0329185 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| 2.7393e+00| -1.764878| 0.454105| 0.056364| 3.704228| -0.551627|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.6844e+00| -1.601678| 0.768552| 0.497187| 3.871933| -0.295784|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.6639e+00| -1.630268| 0.891975| 0.713693| 3.838956| 1.702462|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 2.7022e+00| -1.744248| 0.878715| 0.743771| 3.718831| -8.900276|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.7058e+00| -1.696893| 0.776009| 0.664214| 3.767031| -5.371341|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.69689| < -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 = 9000
CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.247207e+09, tgt = 6.247207e+09, diff = 3.221403e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 9000
CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.100569e+09, tgt = 6.100569e+09, diff = 2.289438e-01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 9000
CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.124625e+07, tgt = 6.124625e+07, diff = 1.490116e-08
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 13
Number of data points = 9000
CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.121854e+07, tgt = 6.121854e+07, diff = 7.450581e-09
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 large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
Running mASTROS......
==> Running ASTROS post-analysis...
real 3m25.135s
user 5m5.477s
sys 2m56.721s
+ 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
=================================================
All tests pass!
[GNU C Compiler (gcc)] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/LINUX64')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/LINUX64')
[Clang] Skipping post processing
[Clang] No filter has been set, publishing all 0 issues
[Clang] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.6,CAPS/training,LINUX64,reynolds)
[Static Analysis] Using reference build 'ESP_UndefinedCaps/CASREV=7.6,ESPTEST=CAPS/training,ESP_ARCH=LINUX64,buildnode=reynolds #171' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1
[Static Analysis] -> All quality gates have been passed
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_UndefinedCaps/CASREV=7.6,ESPTEST=CAPS/training,ESP_ARCH=LINUX64,buildnode=reynolds #172'.
[Checks API] No suitable checks publisher found.
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] done
Finished: SUCCESS
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