[Kamranh01]

Hi, I seem to be getting an issue with my mesh involving an N-point error but every surface and volume has a physical surface/volume attached to it. I am very confused about how to rectify this error.

Any help would be massively appreciated

[Kamranh01]

here is my gmsh file

// Gmsh project created on Mon Feb 27 15:44:12 2023
SetFactory("OpenCASCADE");

Merge "NACA 0012 CLOSED TRAILING EDGE.STEP";
//+
Delete {
Volume{1};
}
//+
Point(5) = {0, -3000, -650, 1.0};
//+
Point(6) = {0, 3000, -650, 1.0};
//+
Point(7) = {5196.15242271, 3000, 2350, 1.0};
//+
Point(8) = {5196.15242271, -3000, 2350, 1.0};
//+
Line(7) = {5, 6};
//+
Line(8) = {8, 7};
//+
Extrude {{0, 1, 0}, {0, 0, -650}, -2*Pi/3} {
Curve{8};
}
//+
Line(12) = {5, 9};
//+
Line(13) = {5, 8};
//+
Line(14) = {6, 10};
//+
Line(15) = {6, 7};
//+
Curve Loop(6) = {14, -10, -15};
//+
Plane Surface(6) = {6};
//+
Curve Loop(7) = {12, -9, -13};
//+
Plane Surface(7) = {7};
//+
Curve Loop(8) = {13, 8, -15, -7};
//+
Plane Surface(8) = {8};
//+
Curve Loop(9) = {12, 11, -14, -7};
//+
Plane Surface(9) = {9};
//+
Surface Loop(2) = {5, 7, 9, 6, 8};
//+
Volume(1) = {2};
//+
Transfinite Curve {2, 4} = 200 Using Bump 1;
//+
Transfinite Curve {1, 3} = 200 Using Progression 1;
//+
Transfinite Surface {1};
//+
Transfinite Surface {2};
//+
Transfinite Curve {10, 9} = 30 Using Progression 1;
//+
Transfinite Curve {11, 8} = 15 Using Progression 1;
//+
Transfinite Curve {7} = 70 Using Bump 10;
//+
Transfinite Curve {12} = 70 Using Progression 1.04;
//+
Transfinite Curve {13} = 70 Using Progression 1.04;
//+
Transfinite Curve {14} = 70 Using Progression 1.04;
//+
Transfinite Curve {15} = 70 Using Progression 1.04;


//+
Physical Surface("INLET", 16) = {6};
//+
Physical Surface("OUTLET", 17) = {7};
//+
Physical Surface("WALL", 18) = {5};
//+
Physical Surface("SIDE_1", 19) = {8};
//+
Physical Surface("SIDE_2", 20) = {9};
//+
Physical Surface("BLADE", 21) = {1, 2, 3, 4};
//+
Physical Volume("FLUID", 22) = {1};

[Kamranh01]

here is the config file I generated

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: NACA 0012 Rotor %
% Author:K.Hussain %
% Institution: University of Strathclyde %
% Date: Feb 28th, 2023 %
% File Version 7.5.1 "Blackbird" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
SOLVER= NAVIER_STOKES
%
KIND_TURB_MODEL= NONE
%
MATH_PROBLEM= DIRECT
%
RESTART_SOL= NO
%
SYSTEM_MEASUREMENTS= SI
%
% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
MACH_NUMBER= 0.0
%
AOA= 7.0
%
FREESTREAM_PRESSURE= 101327.0
%
FREESTREAM_TEMPERATURE= 288.15
%
FREESTREAM_DENSITY= 1.225
%
FREESTREAM_OPTION= TEMPERATURE_FS
%%
REYNOLDS_NUMBER= 165389.9181
%%
REYNOLDS_LENGTH= 0.05
%%
INIT_OPTION= TD_CONDITIONS
%
REF_DIMENSIONALIZATION= DIMENSIONAL
%%
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
REF_ORIGIN_MOMENT_X = 0.00
%%
REF_ORIGIN_MOMENT_Y = 0.00
%%
REF_ORIGIN_MOMENT_Z = -650.00
%
%
REF_LENGTH= 0.05
%
%
REF_AREA= 0

% --------------------------------- FLUID MODEL -----------------------------------%
%
FLUID_MODEL= IDEAL_GAS
%%
GAMMA_VALUE= 1.4
%%
GAS_CONSTANT= 287.06

%
% --------------------------- VISCOSITY MODEL ---------------------------------%
%
VISCOSITY_MODEL= SUTHERLAND
%%
MU_CONSTANT= 1.716E-5
%%
MU_REF= 1.716E-5
%%
MU_T_REF= 273.15
%%
SUTHERLAND_CONSTANT= 110.4
%
%
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
MARKER_HEATFLUX= ( BLADE, 0.0 )

MARKER_FAR= ( WALL )

MARKER_INTERNAL= ( BLADE )

MARKER_INLET= ( INLET, 288.15, 101327, 0.0, 1.0, 0.0)

MARKER_OUTLET= ( OUTLET, 101327)

MARKER_PERIODIC= ( SIDE_1, SIDE_2, 0.0, 0.0, -650.0, 0.0, 120.0, 0.0, 0.0, 0.0, 0.0 )
%%%
% ------------------------ SURFACES IDENTIFICATION ----------------------------%
%
MARKER_PLOTTING= ( BLADE )
%
%
MARKER_MONITORING= ( BLADE )

%% ------------------------- GRID ADAPTATION STRATEGY --------------------------%

% ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
%
GRID_MOVEMENT= ROTATING_FRAME
%
MACH_MOTION= 0.3456
%
MOTION_ORIGIN= 0.0 0.0 -650.0
%
ROTATION_RATE= 0.0, 62.44, 0.0
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
CFL_NUMBER= 1.0
%%
CFL_ADAPT= NO
%%
CFL_ADAPT_PARAM= ( 0.1, 1.2, 10.0, 1000.0)
%%
RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
%
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
LINEAR_SOLVER= FGMRES
%%
LINEAR_SOLVER_PREC= ILU
%%%
LINEAR_SOLVER_ERROR= 1E-4
%%
LINEAR_SOLVER_ITER= 4.0
%
% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
VENKAT_LIMITER_COEFF= 0.05
LIMITER_ITER= 999999
%
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
CONV_NUM_METHOD_FLOW= JST
%
MUSCL_FLOW= YES
%
ENTROPY_FIX_COEFF= 0.001
%
JST_SENSOR_COEFF= ( 0.5, 0.02 )
%
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
TIME_DISCRE_FLOW= EULER_IMPLICIT
%

% --------------------------- SOLVER CONTROLS --------------------------%
%convergeance criteria

ITER= 999999
%%
CONV_RESIDUAL_MINVAL= -9
%%
CONV_STARTITER= 10
%%
CONV_CAUCHY_ELEMS= 100
%%
CONV_CAUCHY_EPS= 1E-6
%%
CONV_FIELD= DRAG
%%
WINDOW_CAUCHY_CRIT = YES
%%
CONV_WINDOW_FIELD = (TAVG_DRAG, TAVG_LIFT)
%%
CONV_WINDOW_STARTITER = 0
%%
CONV_WINDOW_CAUCHY_EPS = 1E-3
%%
CONV_WINDOW_CAUCHY_ELEMS = 10

%
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
MESH_FILENAME= NACA_0012_Base_Mesh.su2
%
MESH_FORMAT= SU2
%
MESH_OUT_FILENAME= NACA_0012_out.SU2
%
SOLUTION_FILENAME= restart_flow.dat
%
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
TABULAR_FORMAT= CSV
%
OUTPUT_FILES= (PARAVIEW, SURFACE_PARAVIEW, RESTART)
%
CONV_FILENAME= history
%
RESTART_FILENAME= restart_flow.dat
%
RESTART_ADJ_FILENAME= restart_adj.dat
VOLUME_FILENAME= flow
%
VOLUME_ADJ_FILENAME= adjoint
%
VALUE_OBJFUNC_FILENAME= of_eval.dat
%
GRAD_OBJFUNC_FILENAME= of_grad.dat
%
SURFACE_FILENAME= surface_flow
%
SURFACE_ADJ_FILENAME= surface_adjoint
%%
OUTPUT_WRT_FREQ= 100
%
%
WRT_FORCES_BREAKDOWN = YES
%
HISTORY_OUTPUT = (ITER, RMS_RES, AERO_COEFF)

[bigfootedrockmidget]

Have you made sure to deselect "save all points" when saving the su2 file?
After saving, have you checked that the su2 file contains points, connectivities and markers? This is a gmsh problem, not an su2 problem.

[Kamranh01]

yeah, i did bro, I think I managed to resolve it. I think the issue was that the sides of the aerofoil were created using splines when the step file I created was merged and there was a bunch of repeated points, I think I managed to resolve it by defining the lines of the aerofoil as physical curves

[bene_]

Hi everyone,

I've been struggling with GMSH for the last 3 days. I keep getting the same error



"Error in "void CPhysicalGeometry:istributeColoring(const CConfig*, CGeometry*)":
-------------------------------------------------------------------------
Mismatch between NPOIN and number of points listed in mesh file.
Please check the mesh file for correctness.
"



even when I try to mesh the simplest possible geometry and run it in Su2. I have made several attempts, even trying to define the curves as physical surfaces, but no luck.
I'm hoping someone can help. Thanks in advance.


I've attached the .geo and .su2 files.