| 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: 0.5.
Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 4240 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 195.346 m.
Reference origin for moment evaluation is (59.4263, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.
Surface(s) plotted in the output file: BC_1.
Input mesh file name: ../aflr3/aflr3_CAPS.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| PARAVIEW| 250|
| SURFACE_PARAVIEW| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_inviscidWing.dat.
Surface file name: surface_flow_inviscidWing.
Volume file name: flow_inviscidWing.
Restart file name: restart_flow_inviscidWing.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
5428 grid points.
14885 volume elements.
2 surface markers.
9846 boundary elements in index 0 (Marker = BC_1).
12 boundary elements in index 1 (Marker = BC_2).
14885 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: 17.3483. Mean K: 1.87813. Standard deviation K: 2.71872.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 3.00765| 84.5031|
| CV Face Area Aspect Ratio| 1.05339| 7.45559e+07|
| CV Sub-Volume Ratio| 1.04356| 5.25343e+09|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 5428| 1/1.00| 10|
| 1| 1312| 1/4.14| 9.34378|
| 2| 170| 1/7.72| 7.09227|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 97.6729 m.
Wetted area = 8226.89 m^2.
Area projection in the x-plane = 667.857 m^2, y-plane = 414.341 m^2, z-plane = 3911.65 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 = -5.4717 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 221265| 1| m^2/s^2| 221265|
| Velocity-X| 170.123| 1| m/s| 170.123|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 2.9695| 1| m/s| 2.9695|
| Velocity Magnitude| 170.149| 1| m/s| 170.149|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.5|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.4327e-01| 2.018843| 4.393874| 3.777455| 7.501689| 0.755017|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.4435e-01| 4.307876| 6.755463| 6.790895| 9.789972| 1.011181|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.4360e-01| 4.933368| 7.423230| 7.303151| 10.453288| 1.364339|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.4301e-01| 5.869632| 8.366580| 8.323836| 11.372230| 1.326352|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.4188e-01| 7.017346| 9.547418| 9.424921| 12.517427| -13.561602|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 7.01735| < -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).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
==> Total Forces and Moments
--> Cl = -0.422084 Cd = 0.031123
--> Cmx = -0.006395 Cmy = 0.058333 Cmz = -0.002047
--> Cx = 0.038485 Cy = -0.002269 Cz = -0.421476
real 0m6.711s
user 0m3.670s
sys 0m1.896s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
real 0m10.762s
user 0m11.862s
sys 0m1.203s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image 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 = 11079
Number of elements = 22781
Number of triangle elements = 22781
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 11079
Total number of elements = 22781
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 = 11911
Number of elements = 24445
Number of triangle elements = 24445
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 11911
Total number of elements = 24445
real 0m11.077s
user 0m12.621s
sys 0m1.430s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 731
Number of elements = 1779
Number of triangle elements = 1779
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 731
Total number of elements = 1779
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 934
Number of elements = 2228
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 = 3548
Number of elements = 7675
Number of triangle elements = 7675
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3548
Total number of elements = 7675
real 0m9.972s
user 0m11.486s
sys 0m1.427s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image 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 = 1405
Number of elements = 3135
Number of triangle elements = 3135
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 1405
Total number of elements = 3135
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Name = wingTE, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 2096
Number of elements = 4568
Number of triangle elements = 4568
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 2096
Total number of elements = 4568
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 triangle elements = 13689
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 6562
Total number of elements = 13689
real 0m10.786s
user 0m12.434s
sys 0m1.411s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image 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 = 3559
Number of elements = 7459
Number of triangle elements = 7459
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3559
Total number of elements = 7459
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 = 12395
Number of elements = 25258
Number of triangle elements = 25258
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 12395
Total number of elements = 25258
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 = 44950
Number of elements = 90567
Number of triangle elements = 90567
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 44950
Total number of elements = 90567
real 0m14.663s
user 0m18.732s
sys 0m1.469s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image 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 = 8299
Number of elements = 17185
Number of triangle elements = 17185
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 8299
Total number of elements = 17185
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 triangle elements = 0
Number of quadrilateral elements = 74322
----------------------------
Total number of nodes = 72029
Total number of elements = 74322
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 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 triangle elements = 0
Number of quadrilateral elements = 2928
----------------------------
Total number of nodes = 3009
Total number of elements = 2928
real 0m17.112s
user 0m18.681s
sys 0m1.542s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image 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 = 8299
Number of elements = 17185
Number of triangle elements = 17185
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 8299
Total number of elements = 17185
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 = 3890
Number of elements = 8352
Number of triangle elements = 8352
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3890
Total number of elements = 8352
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 triangle elements = 0
Number of quadrilateral elements = 6607
----------------------------
Total number of nodes = 6181
Total number of elements = 6607
real 0m10.616s
user 0m12.295s
sys 0m1.442s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image 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 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 = 6585
Number of elements = 13196
Number of triangle elements = 13196
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 6585
Total number of elements = 13196
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = rootLeadingEdge, index = 3
Getting mesh sizing parameters
Mesh sizing name - rootLeadingEdge
Mesh sizing name - wingSpar1
Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 22194
Number of elements = 22195
Number of triangle elements = 0
Number of quadrilateral elements = 22195
----------------------------
Total number of nodes = 22194
Total number of elements = 22195
real 0m11.599s
user 0m13.194s
sys 0m1.430s
+ status=0
+ set +x
=================================================
data/session09/tess_8_MeshSizing.py passed (as expected)
=================================================
=================================================
tess_MinQuad.py test;
+ python tess_MinQuad.py
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../../data/ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image 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 triangle elements = 0
Number of quadrilateral elements = 387
----------------------------
Total number of nodes = 299
Total number of elements = 387
--> Total Elements 387
real 0m8.746s
user 0m9.939s
sys 0m1.364s
+ status=0
+ set +x
=================================================
solutions/session09/tess_MinQuad.py passed (as expected)
=================================================
=================================================
tess_2k.py test;
+ python tess_2k.py
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../../data/ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image 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 triangle elements = 0
Number of quadrilateral elements = 1189
----------------------------
Total number of nodes = 1289
Total number of elements = 1189
--> Total Elements 1189
real 0m9.506s
user 0m10.649s
sys 0m1.345s
+ status=0
+ set +x
=================================================
solutions/session09/tess_2k.py passed (as expected)
=================================================
=================================================
astros_1_ModalClamped.py test;
+ python astros_1_ModalClamped.py
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
==> Running ASTROS pre-analysis...
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 triangle elements = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes = 235
Total number of elements = 227
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 235
Number of elements = 227
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Load tuple is NULL - No loads applied
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Getting FEA analyses.......
Number of analyses - 1
Analysis name - EigenAnalysis
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!!
Writing analysis cards
Writing constraint cards--all constraints for each subcase
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
Reading Astros OUT file - extracting Eigen-Values!
Number of Eigen-Values = 9
Loading Eigen-Value = 1
Loading Eigen-Value = 2
Loading Eigen-Value = 3
Loading Eigen-Value = 4
Loading Eigen-Value = 5
Loading Eigen-Value = 6
Loading Eigen-Value = 7
Loading Eigen-Value = 8
Loading Eigen-Value = 9
--> Eigen-frequencies:
1 : 0.0357647
2 : 0.102451
3 : 0.102451
4 : 0.159637
5 : 0.159637
6 : 0.215446
7 : 0.215446
8 : 0.350115
9 : 0.350115
real 0m20.662s
user 0m15.009s
sys 0m7.396s
+ status=0
+ set +x
=================================================
data/session10/astros_1_ModalClamped.py passed (as expected)
=================================================
=================================================
astros_2_ModalSupport.py test;
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
+ python astros_2_ModalSupport.py
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
==> Running ASTROS pre-analysis...
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 triangle elements = 0
Number of quadrilateral elements = 227
Body 2 (of 2)
Number of nodes = 1
Number of elements = 0
Number of triangle elements = 0
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 236
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 = ribRootPoint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 1
Name = ribRoot, index = 1
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Name = ribSupport, index = 6
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 235
Number of elements = 227
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 227
Setting FEA Data
Mesh for body = 1
Number of nodal coordinates = 1
Number of elements = 1
Elemental Nodes = 1
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 0
Combining multiple FEA meshes!
Combined Number of nodal coordinates = 236
Combined Number of elements = 228
Combined Elemental Nodes = 1
Combined Elemental Rods = 0
Combined Elemental Tria3 = 0
Combined Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 6
Property name - leftWingSkin
Property name - ribSupport
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - ribRootPoint
No "constraintType" specified for Constraint tuple ribRootPoint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple ribRootPoint, going to use constraint name
Done getting FEA constraints
Getting FEA supports.......
Number of supports - 1
Support name - ribRootPoint
No "groupName" specified for Support tuple ribRootPoint, going to use support name
Done getting FEA supports
Getting FEA connections.......
Number of connection tuples - 1
Connection name - ribRoot
No "groupName" specified for Connection tuple ribRoot!
Looking for automatic connections from the use of capsConnectLink for ribRoot
19 automatic connections were made for capsConnect ribRoot (node id 236)
Done getting FEA connections
Load tuple is NULL - No loads applied
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Getting FEA analyses.......
Number of analyses - 1
Analysis name - EigenAnalysis
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing connection cards - appending mesh file
Writing Astros instruction file....
Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!!
Writing analysis cards
Writing constraint cards--all constraints for each subcase
Writing support cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
Reading Astros OUT file - extracting Eigen-Values!
Number of Eigen-Values = 10
Loading Eigen-Value = 1
Loading Eigen-Value = 2
Loading Eigen-Value = 3
Loading Eigen-Value = 4
Loading Eigen-Value = 5
Loading Eigen-Value = 6
Loading Eigen-Value = 7
Loading Eigen-Value = 8
Loading Eigen-Value = 9
Loading Eigen-Value = 10
--> Eigen-frequencies:
1 : 0.0357647
2 : 0.0365801
3 : 0.102451
4 : 0.102453
5 : 0.159637
6 : 0.1611
7 : 0.215446
8 : 0.215462
9 : 0.350115
10: 0.351196
real 0m16.201s
user 0m13.762s
sys 0m4.604s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
==> Running ASTROS pre-analysis...
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 triangle elements = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes = 235
Total number of elements = 227
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 235
Number of elements = 227
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 2
Load name - leftPointLoad
No "groupName" specified for Load tuple leftPointLoad, going to use load name
Load name - ritePointLoad
No "groupName" specified for Load tuple ritePointLoad, going to use load name
Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
--> Maximum displacements:
--> Tmax 43461.879162311016
--> T1max 738.595
--> T2max 3686.25
--> T3max 43363.8
real 0m10.078s
user 0m10.825s
sys 0m1.679s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
==> Running ASTROS pre-analysis...
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 triangle elements = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes = 235
Total number of elements = 227
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = wingSpar1, index = 3
Name = leftWingSkin, index = 4
Name = riteWingSkin, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 235
Number of elements = 227
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Aluminum
No "materialType" specified for Material tuple Aluminum, defaulting to "Isotropic"
Material name - Graphite_epoxy
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 2
Load name - leftPointLoad
No "groupName" specified for Load tuple leftPointLoad, going to use load name
Load name - ritePointLoad
No "groupName" specified for Load tuple ritePointLoad, going to use load name
Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
==> Running mASTROS...
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
--> Maximum displacements:
--> Tmax 12131.654370141774
--> T1max 275.241
--> T2max 1005.74
--> T3max 12103.5
real 0m10.174s
user 0m10.872s
sys 0m1.664s
+ 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
==> Loading geometry from file "../ESP/wing3.csm"...
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
==> Running Nastran pre-analysis...
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = Wing, index = 1
Name = wingSpar2, index = 2
Name = wingRib, index = 3
Name = riteWingSkin, index = 4
Name = wingSpar1, index = 5
Name = leftWingSkin, index = 6
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = wingSpar2, index = 1
Name = wingSpar1, index = 2
Name = leadingEdge, index = 3
Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 4)
Getting surface mesh for body 2 (of 4)
Getting surface mesh for body 3 (of 4)
Getting surface mesh for body 4 (of 4)
Body 1 (of 4)
Number of nodes = 11
Number of elements = 6
Number of triangle elements = 0
Number of quadrilateral elements = 6
Body 2 (of 4)
Number of nodes = 11
Number of elements = 6
Number of triangle elements = 0
Number of quadrilateral elements = 6
Body 3 (of 4)
Number of nodes = 11
Number of elements = 6
Number of triangle elements = 0
Number of quadrilateral elements = 6
Body 4 (of 4)
Number of nodes = 939
Number of elements = 1094
Number of triangle elements = 0
Number of quadrilateral elements = 1094
----------------------------
Total number of nodes = 972
Total number of elements = 1112
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 6
Name = Wing, index = 1
Name = wingSpar2, index = 2
Name = wingRib, index = 3
Name = riteWingSkin, index = 4
Name = wingSpar1, index = 5
Name = leftWingSkin, index = 6
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
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 11
Number of elements = 6
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 6
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
Setting FEA Data
Mesh for body = 1
Number of nodal coordinates = 11
Number of elements = 6
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 6
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
Setting FEA Data
Mesh for body = 2
Number of nodal coordinates = 11
Number of elements = 6
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 6
Setting FEA Data
Mesh for body = 3
Number of nodal coordinates = 939
Number of elements = 1094
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 1094
Combining multiple FEA meshes!
Combined Number of nodal coordinates = 972
Combined Number of elements = 1112
Combined Elemental Nodes = 0
Combined Elemental Rods = 0
Combined Elemental Tria3 = 0
Combined Elemental Quad4 = 1112
Getting vortex lattice surface data
VLM surface name - upperWing
Done getting vortex lattice surface data
Getting FEA vortex lattice mesh
Surface 1: Number of points found for aero-spline = 108
Surface 2: Number of points found for aero-spline = 108
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Load tuple is NULL - No loads applied
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
Mass_Increment tuple is NULL - No mass increments 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 mass increment set
Writing Nastran instruction file....
Warning: No loads specified for case Flutter!!!!
Writing mass increment cards
Writing aero card
Writing analysis cards, 0
Writing constraint ADD cards
Writing constraint cards
Writing material cards
Writing property cards
Writing coordinate system cards
Writing aeroelastic cards
Done writing aeroelastic cards
Done writing files
==> Running Nastran...
sh: nastran: command not found
Traceback (most recent call last):
File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/session10/nastran_5_Flutter.py", line 138, in <module>
nastran.postAnalysis()
File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/pyCAPS/pyCAPS/problem.py", line 2159, in postAnalysis
self._analysisObj.postAnalysis()
File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed
return func(*args, **kwargs)
^^^^^^^^^^^^^^^^^^^^^
File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/pyCAPS/pyCAPS/caps.py", line 2914, in postAnalysis
if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs))
^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus
raise CAPSError(status, msg=msg, errors=errors)
pyCAPS.caps.CAPSError: CAPS_IOERR:
================================================================================
nastranAIM.c:3037 in aimPostAnalysis():
Error: Unable to open file: nastran_modal.f06
================================================================================
real 0m9.426s
user 0m10.011s
sys 0m1.782s
+ status=1
+ set +x
=================================================
data/session10/nastran_5_Flutter.py failed (as NOT expected)
=================================================
=================================================
aeroelastic_2_Iterative_SU2_Astros.py test;
+ python aeroelastic_2_Iterative_SU2_Astros.py
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
Information: Dynamic Loader for scribeWake.so not found
dlopen(scribeWake.so, 130): image not found
==> 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 9.17.15
AFLR2 : Version Date 04/23/24 @ 12:51AM
AFLR2 : Compile OS Darwin 23.4.0 x86_64
AFLR2 : Compile Date 04/23/24 @ 11:49AM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR4 : ---------------------------------------
AFLR4 : AFLR4 LIBRARY
AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4 : Version Number 11.5.14
AFLR4 : Version Date 04/18/24 @ 12:45PM
AFLR4 : Compile OS Darwin 23.4.0 x86_64
AFLR4 : Compile Date 04/23/24 @ 11:49AM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.25
EGADS : OpenCASCADE Version 7.8.0
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 : QC = Face Quad Combination Flag
EGADS : IER = Face Isolated Edge Refinement Flag
EGADS : ER = Face Edge Refinement Factor
EGADS : Not applicable for Faces with a FarField Grid BC.
EGADS : SF = Face Scale Factor
EGADS : Not applicable for Faces with a FarField Grid BC.
EGADS : Face Body QC IER ER Scale Neighbor
EGADS : ID Active ID Flag Flag Weight Factor Faces
EGADS : 1 Yes 0 0 1 1 1 2 3 4
EGADS : 2 Yes 0 0 1 1 1 1 3 5
EGADS : 3 Yes 0 0 1 1 1 1 2
EGADS : 4 Yes 0 0 1 1 1 1 5 6
EGADS : 5 Yes 0 0 1 1 1 2 4 6
EGADS : 6 Yes 0 0 1 1 1 4 5
EGADS : 7 Yes 1 0 1 NA NA 9 10 11 12
EGADS : 8 Yes 1 0 1 NA NA 9 10 11 12
EGADS : 9 Yes 1 0 1 NA NA 7 8 11 12
EGADS : 10 Yes 1 0 1 NA NA 7 8 11 12
EGADS : 11 Yes 1 0 1 NA NA 7 8 9 10
EGADS : 12 Yes 1 0 1 NA NA 7 8 9 10
EGADS : Face Edges Information
EGADS : Face Edges
EGADS : 1 -1 2 3 -4
EGADS : 2 -3 5 1 -6
EGADS : 3 4 6
EGADS : 4 7 9 -8 -2
EGADS : 5 8 10 -7 -5
EGADS : 6 -9 -10
EGADS : 7 11 12 -13 -14
EGADS : 8 -15 18 17 -16
EGADS : 9 19 15 -20 -11
EGADS : 10 -21 13 22 -17
EGADS : 11 14 21 -18 -19
EGADS : 12 -12 20 16 -22
EGADS : Face Loops Information
EGADS : Face Loops
EGADS : 1 1
EGADS : 2 2
EGADS : 3 3
EGADS : 4 4
EGADS : 5 5
EGADS : 6 6
EGADS : 7 7
EGADS : 8 8
EGADS : 9 9
EGADS : 10 10
EGADS : 11 11
EGADS : 12 12
EGADS : Loop Edges Information
EGADS : Loop Active Edges
EGADS : 1 Yes -1 2 3 -4
EGADS : 2 Yes -3 5 1 -6
EGADS : 3 Yes 4 6
EGADS : 4 Yes 7 9 -8 -2
EGADS : 5 Yes 8 10 -7 -5
EGADS : 6 Yes -9 -10
EGADS : 7 Yes 11 12 -13 -14
EGADS : 8 Yes -15 18 17 -16
EGADS : 9 Yes 19 15 -20 -11
EGADS : 10 Yes -21 13 22 -17
EGADS : 11 Yes 14 21 -18 -19
EGADS : 12 Yes -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
EGADS : Face and Edge Match Information
EGADS : No Face Matches Found
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 = 1.29099
AFLR4 : BL Thickness = 0
AFLR4 : FarField Spacing = 105.147
AFLR4 : Abs Min Surf Spacing = 0.00322749
AFLR4 : Min Surf Spacing = 0.00645497
AFLR4 : Max Surf Spacing = 0.129099
AFLR4 : Global Scale Factor = 5
AFLR4 : Geometry Definition Information
AFLR4 : Definition Definition Composite Grid BC
AFLR4 : ID Type ID Type
AFLR4 : 0 glue-only composite - -
AFLR4 : 1 CAD geometry 0 STD w/BL
AFLR4 : 2 CAD geometry 0 STD w/BL
AFLR4 : 3 CAD geometry 0 STD w/BL
AFLR4 : 4 CAD geometry 0 STD w/BL
AFLR4 : 5 CAD geometry 0 STD w/BL
AFLR4 : 6 CAD geometry 0 STD w/BL
AFLR4 : 7 CAD geometry 0 FARFIELD
AFLR4 : 8 CAD geometry 0 FARFIELD
AFLR4 : 9 CAD geometry 0 FARFIELD
AFLR4 : 10 CAD geometry 0 FARFIELD
AFLR4 : 11 CAD geometry 0 FARFIELD
AFLR4 : 12 CAD geometry 0 FARFIELD
AFLR4 : Define CAD surface definition 1
AFLR4 : Define CAD surface definition 2
AFLR4 : Define CAD surface definition 3
AFLR4 : Define CAD surface definition 4
AFLR4 : Define CAD surface definition 5
AFLR4 : Define CAD surface definition 6
AFLR4 : Define CAD surface definition 7
AFLR4 : Define CAD surface definition 8
AFLR4 : Define CAD surface definition 9
AFLR4 : Define CAD surface definition 10
AFLR4 : Define CAD surface definition 11
AFLR4 : Define CAD surface definition 12
AFLR4 : Surface Grid Generation
AFLR4 : Generate optimal mesh on surface definition 1
AFLR2 : Nodes, Trias,Quads= 1520 2861 0
AFLR4 : Nodes, Trias,Quads= 939 1699 0
AFLR4 : Generate optimal mesh on surface definition 2
AFLR2 : Nodes, Trias,Quads= 1511 2844 0
AFLR4 : Nodes, Trias,Quads= 900 1622 0
AFLR4 : Generate optimal mesh on surface definition 3
AFLR2 : Nodes, Trias,Quads= 46 62 0
AFLR4 : Nodes, Trias,Quads= 40 50 0
AFLR4 : Generate optimal mesh on surface definition 4
AFLR2 : Nodes, Trias,Quads= 1528 2877 0
AFLR4 : Nodes, Trias,Quads= 929 1679 0
AFLR4 : Generate optimal mesh on surface definition 5
AFLR2 : Nodes, Trias,Quads= 1511 2844 0
AFLR4 : Nodes, Trias,Quads= 895 1612 0
AFLR4 : Generate optimal mesh on surface definition 6
AFLR2 : Nodes, Trias,Quads= 46 62 0
AFLR4 : Nodes, Trias,Quads= 40 50 0
AFLR4 : Generate optimal mesh on surface definition 7
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 8
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 9
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 10
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 11
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
AFLR4 : Generate optimal mesh on surface definition 12
AFLR2 : Nodes, Trias,Quads= 5 4 0
AFLR4 : Nodes, Trias,Quads= 4 2 0
DGEOM : Add surface definitions to composite definition 0
DGEOM : Glue composite surface definition 0
DGEOM : Nodes,Faces,BEdges= 3366 6724 786
AFLR4 : Auto Mode Turned OFF
OVERALL : CPU Time = 0.100 seconds
Body 1 (of 2)
Number of nodes = 3358
Number of elements = 6712
Number of triangle elements = 6712
Number of quadrilateral elements = 0
Body 2 (of 2)
Number of nodes = 8
Number of elements = 12
Number of triangle elements = 12
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3366
Total number of elements = 6724
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = leftWing, index = 1
Name = riteWing, index = 2
Name = Farfield, index = 3
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Wing, index = 1
Name = Farfield, index = 2
Getting volume mesh
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
UG PARAM : mrecm = 3
UG PARAM : mrecqm = 3
UG PARAM : mpfrmt = 0
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.17.15
AFLR2 : Version Date 04/23/24 @ 12:51AM
AFLR2 : Compile OS Darwin 23.4.0 x86_64
AFLR2 : Compile Date 04/23/24 @ 11:49AM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR4 : ---------------------------------------
AFLR4 : AFLR4 LIBRARY
AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4 : Version Number 11.5.14
AFLR4 : Version Date 04/18/24 @ 12:45PM
AFLR4 : Compile OS Darwin 23.4.0 x86_64
AFLR4 : Compile Date 04/23/24 @ 11:49AM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.25
EGADS : OpenCASCADE Version 7.8.0
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 : QC = Face Quad Combination Flag
EGADS : IER = Face Isolated Edge Refinement Flag
EGADS : ER = Face Edge Refinement Factor
EGADS : Not applicable for Faces with a FarField Grid BC.
EGADS : SF = Face Scale Factor
EGADS : Not applicable for Faces with a FarField Grid BC.
EGADS : Face Body QC IER ER Scale Neighbor
EGADS : ID Active ID Flag Flag Weight Factor Faces
EGADS : 1 Yes 0 0 1 1 1 2 3 4
EGADS : 2 Yes 0 0 1 1 1 1 3 5
EGADS : 3 Yes 0 0 1 1 1 1 2
EGADS : 4 Yes 0 0 1 1 1 1 5 6
EGADS : 5 Yes 0 0 1 1 1 2 4 6
EGADS : 6 Yes 0 0 1 1 1 4 5
EGADS : 7 Yes 1 0 1 NA NA 9 10 11 12
EGADS : 8 Yes 1 0 1 NA NA 9 10 11 12
EGADS : 9 Yes 1 0 1 NA NA 7 8 11 12
EGADS : 10 Yes 1 0 1 NA NA 7 8 11 12
EGADS : 11 Yes 1 0 1 NA NA 7 8 9 10
EGADS : 12 Yes 1 0 1 NA NA 7 8 9 10
EGADS : Face Edges Information
EGADS : Face Edges
EGADS : 1 -1 2 3 -4
EGADS : 2 -3 5 1 -6
EGADS : 3 4 6
EGADS : 4 7 9 -8 -2
EGADS : 5 8 10 -7 -5
EGADS : 6 -9 -10
EGADS : 7 11 12 -13 -14
EGADS : 8 -15 18 17 -16
EGADS : 9 19 15 -20 -11
EGADS : 10 -21 13 22 -17
EGADS : 11 14 21 -18 -19
EGADS : 12 -12 20 16 -22
EGADS : Face Loops Information
EGADS : Face Loops
EGADS : 1 1
EGADS : 2 2
EGADS : 3 3
EGADS : 4 4
EGADS : 5 5
EGADS : 6 6
EGADS : 7 7
EGADS : 8 8
EGADS : 9 9
EGADS : 10 10
EGADS : 11 11
EGADS : 12 12
EGADS : Loop Edges Information
EGADS : Loop Active Edges
EGADS : 1 Yes -1 2 3 -4
EGADS : 2 Yes -3 5 1 -6
EGADS : 3 Yes 4 6
EGADS : 4 Yes 7 9 -8 -2
EGADS : 5 Yes 8 10 -7 -5
EGADS : 6 Yes -9 -10
EGADS : 7 Yes 11 12 -13 -14
EGADS : 8 Yes -15 18 17 -16
EGADS : 9 Yes 19 15 -20 -11
EGADS : 10 Yes -21 13 22 -17
EGADS : 11 Yes 14 21 -18 -19
EGADS : 12 Yes -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
EGADS : Face and Edge Match Information
EGADS : No Face Matches Found
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 = 0.433058
AFLR4 : BL Thickness = 0
AFLR4 : FarField Spacing = 16.9832
AFLR4 : Abs Min Surf Spacing = 0.00108265
AFLR4 : Min Surf Spacing = 0.00216529
AFLR4 : Max Surf Spacing = 0.0433058
AFLR4 : Global Scale Factor = 1
AFLR4 : Geometry Definition Information
AFLR4 : Definition Definition Composite Grid BC
AFLR4 : ID Type ID Type
AFLR4 : 0 glue-only composite - -
AFLR4 : 1 CAD geometry 0 STD
AFLR4 : 2 CAD geometry 0 STD
AFLR4 : 3 CAD geometry 0 STD
AFLR4 : 4 CAD geometry 0 STD
AFLR4 : 5 CAD geometry 0 STD
AFLR4 : 6 CAD geometry 0 STD
AFLR4 : 7 CAD geometry 0 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
AFLR43 : INPUT SURFACE MESH FROM TESS
AFLR43 : Quad Surface Faces= 0
AFLR43 : Tria Surface Faces= 6724
AFLR43 : Nodes = 3366
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
UG PARAM : mrecm = 3
UG PARAM : mrecqm = 3
UG PARAM : mpfrmt = 0
AFLR3 : ---------------------------------------
AFLR3 : AFLR3 LIBRARY
AFLR3 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR3 : TETRAHEDRAL GRID GENERATOR
AFLR3 : Version Number 16.32.50
AFLR3 : Version Date 10/31/23 @ 06:31PM
AFLR3 : Compile OS Darwin 22.6.0 x86_64
AFLR3 : Compile Date 11/01/23 @ 12:19PM
AFLR3 : Copyright 1994-2021, D.L. Marcum
AFLR3 : ---------------------------------------
AFLR3 IC : INPUT SURFACE GRID CHECK
AFLR3 IC : Nodes, Elements = 3366 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 = 0.008 seconds
AFLR3 IG : INITIAL VOLUME GRID GENERATION
AFLR3 IG : Nodes, Elements = 3366 0
AFLR3 IG : Nodes, Elements = 8 10
AFLR3 IG : Nodes, Elements = 674 4728
AFLR3 IG : Nodes, Elements = 1348 9669
AFLR3 IG : Nodes, Elements = 2022 14757
AFLR3 IG : Nodes, Elements = 2696 19981
AFLR3 IG : Nodes, Elements = 3370 24964
AFLR3 IG : Nodes, Elements = 3373 25026
AFLR3 IG : Nodes, Elements = 3373 24949
AFLR3 IG : Nodes, Elements = 3373 24685
AFLR3 IG : Nodes, Elements = 3373 21476
AFLR3 IG : Nodes, Elements = 3373 21475
AFLR3 IG : Nodes, Elements = 3373 24588
AFLR3 IG : Nodes, Elements = 3373 24511
AFLR3 IG : Nodes, Elements = 3373 20065
AFLR3 IG : Nodes, Elements = 3373 20064
AFLR3 IG : Nodes, Elements = 3366 10606
AFLR3 IG : Nodes, Elements = 3366 15327
AFLR3 IG : Nodes, Elements = 3366 8687
AFLR3 IG : Nodes, Elements = 3366 8147
AFLR3 : CPU Time = 0.126 seconds
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
AFLR3 GG : Nodes, Elements = 3366 8147
AFLR3 GG : Nodes, Elements = 3385 8204
AFLR3 GG : Nodes, Elements = 3385 8280
AFLR3 GG : Nodes, Elements = 3385 8103
AFLR3 GG : Nodes, Elements = 3390 8118
AFLR3 GG : Nodes, Elements = 3390 8167
AFLR3 GG : Nodes, Elements = 3390 8139
AFLR3 GG : Nodes, Elements = 3407 8190
AFLR3 GG : Nodes, Elements = 3407 8362
AFLR3 GG : Nodes, Elements = 3407 8267
AFLR3 GG : Nodes, Elements = 3426 8324
AFLR3 GG : Nodes, Elements = 3426 8471
AFLR3 GG : Nodes, Elements = 3426 8402
AFLR3 GG : Nodes, Elements = 3442 8450
AFLR3 GG : Nodes, Elements = 3442 8529
AFLR3 GG : Nodes, Elements = 3442 8487
AFLR3 GG : Nodes, Elements = 3446 8499
AFLR3 GG : Nodes, Elements = 3446 8521
AFLR3 GG : Nodes, Elements = 3446 8509
AFLR3 GG : Nodes, Elements = 3447 8512
AFLR3 GG : Nodes, Elements = 3447 8513
AFLR3 GG : Nodes, Elements = 3447 8512
AFLR3 : CPU Time = 0.023 seconds
AFLR3 QI : QUALITY IMPROVEMENT
AFLR3 QI : Nodes, Elements = 3447 8512
AFLR3 QI : Nodes, Elements = 3440 8478
AFLR3 QI : Nodes, Elements = 3438 8471
AFLR3 QI : Nodes, Elements = 3438 13068
AFLR3 QI : Nodes, Elements = 3438 8962
AFLR3 QI : Nodes, Elements = 3438 8394
AFLR3 QI : Nodes, Elements = 3438 13062
AFLR3 QI : Nodes, Elements = 3438 8843
AFLR3 QI : Nodes, Elements = 3438 8376
AFLR3 QI : Nodes, Elements = 3438 13063
AFLR3 QI : Nodes, Elements = 3438 8926
AFLR3 QI : Nodes, Elements = 3438 8375
AFLR3 QI : Nodes, Elements = 3438 13065
AFLR3 QI : Nodes, Elements = 3438 8840
AFLR3 QI : Nodes, Elements = 3438 8385
AFLR3 QI : Nodes, Elements = 3438 13071
AFLR3 QI : Nodes, Elements = 3438 8924
AFLR3 QI : Nodes, Elements = 3438 8375
AFLR3 QI : Nodes, Elements = 3438 8261
AFLR3 QI : Nodes, Elements = 3460 8342
AFLR3 QI : Nodes, Elements = 3460 12686
AFLR3 QI : Nodes, Elements = 3460 8619
AFLR3 QI : Nodes, Elements = 3460 8221
AFLR3 QI : Nodes, Elements = 3460 11487
AFLR3 QI : Nodes, Elements = 3460 8545
AFLR3 QI : Nodes, Elements = 3460 8197
AFLR3 QI : Nodes, Elements = 3460 8342
AFLR3 : CPU Time = 0.137 seconds
AFLR3 QRG: QUALITY GRID RE-GENERATION
AFLR3 QRG: Nodes, Elements = 3460 8342
AFLR3 : CPU Time = 0.003 seconds
AFLR3 : DONE
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 8342
UG3 : Min, Max Ang = 0.004058 179.4
UG3 : Average Angle = 73.8
UG3 : No. Angle>160.0 = 1611
UG3 : No. Angle>179.9 = 0
UG3 : VOL CHECK
UG3 : Total-Volume = 3.72e+06
UG3 : No. Tet Elems = 8342
UG3 : Min Vol = 1.24e-07
UG3 : Average Vol = 446
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 = 8342
UG3 : Min, Max Q = 1.41e-05 0.995
UG3 : Average Q = 0.0455
UG3 : No. Q< 0.1 = 7632
UG3 : No. Q< 0.01 = 6475
OVERALL : CPU Time = 0.302 seconds
UG3 : DIHEDRAL ANGLE CHECK
UG3 : No. Tet Elems = 8342
UG3 : Min, Max Ang = 0.004058 179.4
UG3 : Average Angle = 73.8
UG3 : No. Angle>160.0 = 1611
UG3 : No. Angle>179.9 = 0
UG3 : VOL CHECK
UG3 : Total-Volume = 3.72e+06
UG3 : No. Tet Elems = 8342
UG3 : Min Vol = 1.24e-07
UG3 : Average Vol = 446
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 = 8342
UG3 : Min, Max Q = 0.000225 1
UG3 : Average Q = 0.112
UG3 : No. Q< 0.1 = 7000
UG3 : No. Q< 0.01 = 5222
UG3 : CPU Time = 0.000 seconds
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.25
EGADS : OpenCASCADE Version 7.8.0
EGADS : ---------------------------------------
EGADS : CREATE EGADS TESS FROM AFLR3 DATA
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 1
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 2
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 3
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 4
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 5
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 6
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 7
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 8
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 9
EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 10
EGADS : CREATING TESSELLATION FOR BODY 0 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 FACE NODE MAP
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 1
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 2
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 3
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 4
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 5
EGADS : CHECKING NODE MAP FOR BODY 0 FACE 6
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 7
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 8
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 9
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 10
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 11
EGADS : CHECKING NODE MAP FOR BODY 1 FACE 12
Volume mesh:
Number of nodes = 3460
Number of elements = 15066
Number of triangles = 6724
Number of quadrilatarals = 0
Number of tetrahedrals = 8342
Number of pyramids = 0
Number of prisms = 0
Number of hexahedrals = 0
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wing
Done getting CFD boundary conditions
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.5.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
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_CAPS.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| TECPLOT| 250|
| SURFACE_TECPLOT| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface file name: surface_flow_aeroelasticIterative.
Volume file name: flow_aeroelasticIterative.
Restart file name: restart_flow_aeroelasticIterative.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
3460 grid points.
8342 volume elements.
2 surface markers.
6712 boundary elements in index 0 (Marker = BC_1).
12 boundary elements in index 1 (Marker = BC_2).
8342 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: 219.454. Mean K: 28.4535. Standard deviation K: 38.6679.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 0.0682672| 83.7513|
| CV Face Area Aspect Ratio| 1.01432| 6.97914e+07|
| CV Sub-Volume Ratio| 1| 1.70741e+09|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 3460| 1/1.00| 10|
| 1| 864| 1/4| 9.44577|
| 2| 217| 1/3.98| 8.93944|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 19.2896 m^2.
Area projection in the x-plane = 1.51633 m^2, y-plane = 0.798925 m^2, z-plane = 9.19279 m^2.
Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399893 m.
Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0331205 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 211798| 1| m^2/s^2| 211798|
| Velocity-X| 100.087| 1| m/s| 100.087|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 0| 1| m/s| 0|
| Velocity Magnitude| 100.087| 1| m/s| 100.087|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 7.7275e-02| -0.680855| 1.612262| 0.939891| 4.788251| 1.952671|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 7.7141e-02| 1.810975| 4.398221| 3.843131| 7.299741| 1.703889|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 7.6649e-02| 1.725465| 4.461075| 4.043557| 7.211044| 1.391445|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 7.6141e-02| 1.815075| 4.395241| 4.143837| 7.283793| 1.144820|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 7.6346e-02| 1.957232| 4.493318| 4.104519| 7.428846| 0.843001|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 1.95723| < -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).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
==> Running SU2 post-analysis...
==> Running ASTROS pre-analysis...
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = 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 triangle elements = 0
Number of quadrilateral elements = 346
----------------------------
Total number of nodes = 265
Total number of elements = 346
Mapping Csys attributes ................
Number of unique Csys attributes = 2
Name = leftWingSkin, index = 1
Name = riteWingSkin, index = 2
Getting FEA coordinate systems.......
Number of coordinate systems - 2
Coordinate system name - leftWingSkin
Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
Number of unique capsConstraint attributes = 1
Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
Number of unique capsLoad attributes = 2
Name = ritePointLoad, index = 1
Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
Number of unique capsBound attributes = 4
Name = upperWing, index = 1
Name = lowerWing, index = 2
Name = leftTip, index = 3
Name = riteTip, index = 4
Mapping capsConnect attributes ................
Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = wingSpar2, index = 1
Name = wingRib, index = 2
Name = riteWingSkin, index = 3
Name = wingSpar1, index = 4
Name = leftWingSkin, index = 5
Setting FEA Data
Mesh for body = 0
Number of nodal coordinates = 265
Number of elements = 346
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 0
Elemental Quad4 = 346
Aero_Reference value is NULL - No aero reference parameters set
Getting FEA materials.......
Number of materials - 2
Material name - Madeupium
Material name - Unobtainium
No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
Done getting FEA materials
Getting FEA properties.......
Number of properties - 5
Property name - leftWingSkin
Property name - riteWingSkin
Property name - wingRib
Property name - wingSpar1
Property name - wingSpar2
Done getting FEA properties
Updating mesh element types based on properties input
Getting FEA constraints.......
Number of constraints - 1
Constraint name - rootConstraint
No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Getting FEA loads.......
Number of loads - 1
Load name - pressureAero
No "groupName" specified for Load tuple pressureAero, going to use load name
Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used
Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL
Getting FEA analyses.......
Number of analyses - 1
Analysis name - Default
Done getting FEA analyses
CAPS Info: Reparameterization Bound -> upperWing -- nu, nv = 33 129
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 3358
CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.261419e+09, tgt = 6.261419e+09, diff = 4.959123e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 3358
CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
Rank 0: src = 6.059260e+09, tgt = 6.059260e+09, diff = 4.587736e-01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 3358
CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.175460e+07, tgt = 6.175460e+07, diff = 1.490116e-08
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 3358
CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
Rank 0: src = 6.182092e+07, tgt = 6.182092e+07, diff = 7.450581e-09
Extracting external pressure loads from data transfer....
TransferName = upperWing
Number of Elements = 96 (total = 96)
Extracting external pressure loads from data transfer....
TransferName = lowerWing
Number of Elements = 96 (total = 192)
Extracting external pressure loads from data transfer....
TransferName = leftTip
Number of Elements = 10 (total = 202)
Extracting external pressure loads from data transfer....
TransferName = riteTip
Number of Elements = 10 (total = 212)
Writing Astros grid and connectivity file (in free field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
Running mASTROS......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
==> Running ASTROS post-analysis...
==> Running SU2 pre-analysis...
Writing boundary flags
- bcProps.surfaceProp[0].surfaceType = 3
- bcProps.surfaceProp[1].surfaceType = 1
Done boundary flags
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.5.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Mesh Deformation Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../aflr3/aflr3_CAPS.su2
---------------- Grid deformation parameters ( Zone 0 ) ----------------
Grid deformation using a linear elasticity method.
-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: ../aflr3/aflr3_CAPS.su2.
Cell stiffness scaled by distance to nearest solid surface.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| BC_2|
+-----------------------------------------------------------------------+
Three dimensional problem.
3460 grid points.
8342 volume elements.
2 surface markers.
6712 boundary elements in index 0 (Marker = BC_1).
12 boundary elements in index 1 (Marker = BC_2).
8342 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).
Completed in 0.169343 seconds on 1 core.
----------------------- Write deformed grid files -----------------------
|SU2 mesh |../aflr3/aflr3_CAPS.su2 |
|CSV file |surface_deformed.csv |
|Tecplot binary |volume_deformed.szplt |
|Tecplot binary surface |surface_deformed.szplt |
Adding any FFD information to the SU2 file.
------------------------- Finalize Solver -------------------------
Deleted CNumerics container.
Deleted CSolver container.
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.
------------------------- Exit Success (SU2_DEF) ------------------------
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
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_CAPS.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| TECPLOT| 250|
| SURFACE_TECPLOT| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface file name: surface_flow_aeroelasticIterative.
Volume file name: flow_aeroelasticIterative.
Restart file name: restart_flow_aeroelasticIterative.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
3460 grid points.
8342 volume elements.
2 surface markers.
6712 boundary elements in index 0 (Marker = BC_1).
12 boundary elements in index 1 (Marker = BC_2).
8342 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 4824 TETRAHEDRON volume elements.
There has been a re-orientation of 4146 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 5.71106e+15.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 1.43788. Mean K: 0.00686311. Standard deviation K: 0.0410634.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 0.00256425| 69.2196|
| CV Face Area Aspect Ratio| 2| 8.37665e+06|
| CV Sub-Volume Ratio| 1.0006| 1.30971e+13|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 3460| 1/1.00| 10|
| 1| 876| 1/3.95| 9.48929|
| 2| 220| 1/3.98| 8.98045|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 53155.8 m.
Wetted area = 1.53949e+11 m^2.
Area projection in the x-plane = 1.09339e+11 m^2, y-plane = 1.3391e+10 m^2, z-plane = 3.56108e+09 m^2.
Max. coordinate in the x-direction = 329.068 m, y-direction = 53155.8 m, z-direction = 1.2981e+06 m.
Min. coordinate in the x-direction = -40864.8 m, y-direction = -79239 m, z-direction = -13538 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 211798| 1| m^2/s^2| 211798|
| Velocity-X| 100.087| 1| m/s| 100.087|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 0| 1| m/s| 0|
| Velocity Magnitude| 100.087| 1| m/s| 100.087|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 7.7658e-02| 11.259688| 14.243536| 14.075837| 16.728793| 0.039929|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 7.8182e-02| 11.326154| 13.921064| 13.900790| 16.578698| 0.038179|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 7.8458e-02| 11.280518| 13.954488| 13.817958| 16.593313| 0.036639|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 7.8306e-02| 11.492466| 13.964948| 14.018248| 16.737994| 0.035772|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 7.8112e-02| 11.449575| 13.956605| 13.972222| 16.809876| 0.035244|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 11.4496| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticIterative.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|CSV file |surface_flow_aeroelasticIterative.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary |flow_aeroelasticIterative.szplt |
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary surface |surface_flow_aeroelasticIterative.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
+-----------------------------------------------------------------------+
Warning: there are 437 non-physical points in the solution.
Warning: 188 reconstructed states for upwinding are non-physical.
--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
==> Running SU2 post-analysis...
==> Running ASTROS pre-analysis...
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 3358
CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
Rank 0: src = 4.344226e+09, tgt = 4.344226e+09, diff = 1.266706e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 3358
CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
Rank 0: src = 3.669256e+09, tgt = 3.669256e+09, diff = 2.978177e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 3358
CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
Rank 0: src = 2.732655e+07, tgt = 2.732655e+07, diff = 1.175702e-04
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
Number of variables = 16
Number of data points = 3358
CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
Rank 0: src = 1.793375e+07, tgt = 1.793375e+07, diff = 0.000000e+00
Extracting external pressure loads from data transfer....
TransferName = upperWing
Number of Elements = 96 (total = 96)
Extracting external pressure loads from data transfer....
TransferName = lowerWing
Number of Elements = 96 (total = 192)
Extracting external pressure loads from data transfer....
TransferName = leftTip
Number of Elements = 10 (total = 202)
Extracting external pressure loads from data transfer....
TransferName = riteTip
Number of Elements = 10 (total = 212)
Writing Astros grid and connectivity file (in free field format) ....
Finished writing Astros grid file
Writing subElement types (if any) - appending mesh file
Writing Astros instruction file....
Writing analysis cards
Writing load ADD cards
Writing constraint cards--each subcase individually
Writing load cards
Writing material cards
Writing property cards
Writing coordinate system cards
Running mASTROS......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
==> Running ASTROS post-analysis...
real 0m25.709s
user 0m23.505s
sys 0m3.100s
+ status=0
+ set +x
=================================================
data/session11/aeroelastic_2_Iterative_SU2_Astros.py passed (as expected)
=================================================
*************************************************
*************************************************
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Did not run examples for:
session07 pointwise
session08 fun3d
session11 fun3d+astros
=================================================
=================================================
Summary of examples NOT finished as expected
data/session10/nastran_5_Flutter.py
See training.log for more details.
=================================================
=================================================
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Build step 'Conditional step (single)' marked build as failure
[GNU C Compiler (gcc)Clang] Skipping execution of recorder since overall result is 'FAILURE'
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] Skipped based on build state FAILURE
Finished: FAILURE
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