| dasssj |
November 3, 2015 03:47 |
Failed to start in prarllel mode
Hi,guys!
I compile SU2(v4.0.1) on windows7 sucessfully, and it works good when run in sigle mode, but ii failed to start in parallel mode.
The MPI I use is MsMPI(Microsoft MPI), and it works well in SU2 v3.2.7 in parallel mode.
The messeage I got is:
Code:
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 4.0.1 "Cardinal" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
| Local date and time: Tue Nov 03 16:25:42 2015. |
-------------------------------------------------------------------------
| SU2 Lead Dev.: Dr. Francisco Palacios, Francisco.D.Palacios@boeing.com|
| Dr. Thomas D. Economon, economon@stanford.edu |
-------------------------------------------------------------------------
| SU2 Developers: |
| - Prof. Juan J. Alonso's group at Stanford University. |
| - Prof. Piero Colonna's group at Delft University of Technology. |
| - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. |
| - Prof. Alberto Guardone's group at Polytechnic University of Milan. |
| - Prof. Rafael Palacios' group at Imperial College London. |
-------------------------------------------------------------------------
| Copyright (C) 2012-2015 SU2, the open-source CFD code. |
| |
| 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 -----------------------
Compressible RANS equations.
Turbulence model: Spalart Allmaras
Mach number: 0.2.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
Reynolds number: 4.7e+006.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference length/area (force coefficient) is 1.
The reference length (moment computation) is 1.
Reference origin (moment computation) is (0.25, 0, 0).
Surface(s) where the force coefficients are evaluated: airfoil.
Surface(s) plotted in the output file: airfoil.
Surface(s) belonging to the Fluid-Structure Interaction problem:
Surface(s) affected by the design variables: airfoil.
Input mesh file name: NACA2412.su2
---------------------- Space Numerical Integration ----------------------
Roe (with entropy fix) solver for the flow inviscid terms.
Second order integration.
Scalar upwind solver (first order) for the turbulence model.
First order integration.
Average of gradients with correction (viscous flow terms).
Average of gradients with correction (viscous turbulence terms).
Gradient computation using Green-Gauss theorem.
---------------------- Time Numerical Integration -----------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
CFL adaptation. Factor down: 1.5, factor up: 0.5, lower limit: 1, upper limit: 20.
Courant-Friedrichs-Lewy number: 2
Euler implicit time integration for the turbulence model.
------------------------- Convergence Criteria --------------------------
Maximum number of iterations: 99999.
Cauchy criteria for Lift using 100 elements and epsilon 1e-006.
Start convergence criteria at iteration 10.
-------------------------- Output Information ---------------------------
Writing a flow solution every 250 iterations.
Writing the convergence history every 1 iterations.
The output file format is Tecplot ASCII (.dat).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown.dat.
Surface flow coefficients file name: surface_flow.
Flow variables file name: flow.
Restart flow file name: restart_flow.dat.
------------------- Config File Boundary Information --------------------
Far-field boundary marker(s): far.
Constant heat flux wall boundary marker(s): airfoil.
---------------------- Read Grid File Information -----------------------
Two dimensional problem.
37350 points before parallel partitioning.
Performing linear partitioning of the grid nodes.
37101 interior elements before parallel partitioning.
Distributing elements across all ranks.
Calling the partitioning functions.
Building the graph adjacency structure.
2 surface markers.
249 boundary elements in index 0 (Marker = airfoil).
249 boundary elements in index 1 (Marker = far).
Communicating partition data and creating halo layers.
37101 interior elements including halo cells.
37101 quadrilaterals.
37350 vertices including ghost points.
Establishing MPI communication patterns.
------------------------- Geometry Preprocessing ------------------------
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
Identifying edges and vertices.
Computing centers of gravity.
Setting the control volume structure.
job aborted:
[ranks] message
[0-4] terminated
[5] process exited without calling finalize
[6-11] terminated
---- error analysis -----
[5] on admin-pc17
E:\SSJ\SU2_v4.0.1\SU2_CFD ended prematurely and may have crashed. exit code 0xc0000005
---- error analysis -----
SU2 process was terminated by signal '3'
Any body know how to fix this peoblem?
Thanks in advance!
Jason |
