CFD Online Discussion Forums - Segmentation 11 fault

Hi,

I'm trying to run a su2 simulation for a simple structured mesh (cube with a cylindrical hole inside).
However, while running, it stops after reading all the boundary elements (corresponding to the physical surfaces of the mesh).

Can someone help me with this issue?

N.B. I'm using the following configuration file:
"%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% %

% SU2 configuration file %

% Case description: ONERA M6 wing in inviscid, transonic flow %

% Author: Thomas D. Economon %

% Institution: Stanford University %

% Date: 2015.08.25 %

% File Version 4.2.0 "Cardinal" %

% %

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations (EULER, NAVIER_STOKES)
PHYSICAL_PROBLEM= EULER
%
% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= NO

% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.8
%
% Angle of attack (degrees)
AoA= 0
%
% Side-slip angle (degrees)
SIDESLIP_ANGLE= 0.0
%
% Free-stream pressure (101325.0 N/m^2 by default, only for Euler equations)
FREESTREAM_PRESSURE= 101325.0
%
% Free-stream temperature (288.15 K by default)
FREESTREAM_TEMPERATURE= 288.15

% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference length for pitching, rolling, and yaMAIN_BOX non-dimensional moment
REF_LENGTH_MOMENT= 1.0
%
% Reference area for force coefficients (0 implies automatic calculation)
REF_AREA= 0
%
% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_ONE

% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%

%

% Marker of the Euler boundary (0 implies no marker)

MARKER_EULER= ( Inlet,Top, Bottom, Sides, Inside, Outlet )

%

% Marker of the far field (0 implies no marker)

MARKER_FAR= ( Inlet )

%

% Marker of symmetry boundary (0 implies no marker)

MARKER_SYM= ( Inlet)

% ------------------------ SURFACES IDENTIFICATION ----------------------------%

%

% Marker(s) of the surface in the surface flow solution file

MARKER_PLOTTING = ( Inlet,Top, Bottom, Sides, Inside, Outlet)

%

% Marker(s) of the surface where the non-dimensional coefficients are evaluated.

MARKER_MONITORING = ( Inlet,Top, Bottom, Sides, Inside, Outlet)

%

% Marker(s) of the surface where obj. func. (design problem) will be evaluated

MARKER_DESIGNING = ( Inlet,Top, Bottom, Sides, Inside, Outlet)

% ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%

%

% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)

NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES

%

% Courant-Friedrichs-Lewy condition of the finest grid

CFL_NUMBER= 5.0

%

% Adaptive CFL number (NO, YES)

CFL_ADAPT= NO

%

% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,

% CFL max value )

CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )

%

% Runge-Kutta alpha coefficients

RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )

%

% Number of total iterations

EXT_ITER= 99999

%

% Linear solver for the implicit formulation (BCGSTAB, FGMRES)

LINEAR_SOLVER= FGMRES

%

% Min error of the linear solver for the implicit formulation

LINEAR_SOLVER_ERROR= 1E-6

%

% Max number of iterations of the linear solver for the implicit formulation

LINEAR_SOLVER_ITER= 2

% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%

%

% Reference element length for computing the slope and sharp edges limiters.

REF_ELEM_LENGTH= 0.1

%

% Coefficient for the limiter

LIMITER_COEFF= 0.3

%

% Coefficient for the sharp edges limiter

SHARP_EDGES_COEFF= 3.0

%

% Reference coefficient (sensitivity) for detecting sharp edges.

REF_SHARP_EDGES= 3.0

%

% Remove sharp edges from the sensitivity evaluation (NO, YES)

SENS_REMOVE_SHARP= YES

% -------------------------- MULTIGRID PARAMETERS -----------------------------%

%

% Multi-Grid Levels (0 = no multi-grid)

MGLEVEL= 3

%

% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)

MGCYCLE= W_CYCLE

%

% Multi-Grid PreSmoothing Level

MG_PRE_SMOOTH= ( 1, 2, 3, 3 )

%

% Multi-Grid PostSmoothing Level

MG_POST_SMOOTH= ( 0, 0, 0, 0 )

%

% Jacobi implicit smoothing of the correction

MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )

%

% Damping factor for the residual restriction

MG_DAMP_RESTRICTION= 0.9

%

% Damping factor for the correction prolongation

MG_DAMP_PROLONGATION= 0.9

% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
% TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= JST
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_FLOW= 2ND_ORDER
%
% Slope limiter (VENKATAKRISHNAN, MINMOD)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
% 1st, 2nd and 4th order artificial dissipation coefficients
AD_COEFF_FLOW= ( 0.15, 0.5, 0.02 )
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_FLOW= EULER_IMPLICIT

% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, ROE)
CONV_NUM_METHOD_ADJFLOW= JST
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_ADJFLOW= 2ND_ORDER
%
% Slope limiter (VENKATAKRISHNAN, SHARP_EDGES)
SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN
%
% 1st, 2nd, and 4th order artificial dissipation coefficients
AD_COEFF_ADJFLOW= ( 0.15, 0.0, 0.02 )
%
% Reduction factor of the CFL coefficient in the adjoint problem
CFL_REDUCTION_ADJFLOW= 0.5
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT)
TIME_DISCRE_ADJFLOW= EULER_IMPLICIT

% --------------------------- CONVERGENCE PARAMETERS --------------------------&
%
% Convergence criteria (CAUCHY, RESIDUAL)
CONV_CRITERIA= RESIDUAL
%
% Residual reduction (order of magnitude with respect to the initial value)
RESIDUAL_REDUCTION= 8
%
% Min value of the residual (log10 of the residual)
RESIDUAL_MINVAL= -12
%
% Start convergence criteria at iteration number
STARTCONV_ITER= 25
%
% Number of elements to apply the criteria
CAUCHY_ELEMS= 100
%
% Epsilon to control the series convergence
CAUCHY_EPS= 1E-10
%
% Function to apply the criteria (LIFT, DRAG, NEARFIELD_PRESS, SENS_GEOMETRY,
% SENS_MACH, DELTA_LIFT, DELTA_DRAG)
CAUCHY_FUNC_FLOW= DRAG

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
% Mesh input file
MESH_FILENAME= July_new_mesh.su2
%
% Mesh output file
MESH_OUT_FILENAME= mesh_out.su2
%
% Restart flow input file
SOLUTION_FLOW_FILENAME= solution_flow.dat
%
% Restart adjoint input file
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
% Mesh input file format (SU2)
MESH_FORMAT= SU2
%
% Output file format (PARAVIEW, TECPLOT)
OUTPUT_FORMAT= TECPLOT
%
% Output file convergence history
CONV_FILENAME= history
%
% Output file restart flow
RESTART_FLOW_FILENAME= restart_flow.dat
%
% Output file restart adjoint
RESTART_ADJ_FILENAME= restart_adj.dat
%
% Output file flow (w/o extension) variables
VOLUME_FLOW_FILENAME= flow
%
% Output file adjoint (w/o extension) variables
VOLUME_ADJ_FILENAME= adjoint
%
% Output Objective function gradient (using continuous adjoint)
GRAD_OBJFUNC_FILENAME= of_grad.dat
%
% Output file surface flow coefficient (w/o extension)
SURFACE_FLOW_FILENAME= surface_flow
%
% Output file surface adjoint coefficient (w/o extension)
SURFACE_ADJ_FILENAME= surface_adjoint
%
% Writing solution frequency
WRT_SOL_FREQ= 250
%
% Writing convergence history frequency
WRT_CON_FREQ= 1

"