[Kamranh01]

Hi guys, wondering if I could get some help. my project involves using a submerged aerofoil within a cylindrical section of far-field to simulate a rotor in conditions replicating earth and martian atmospheres

My first issue involves my mesh which was generated within gmsh, despite the two periodic side walls having the same transfinite curves and definitions for some reason the element distributions differ and I have no idea how to make the two separate walls have a symmetrical mesh, is there any way to do so? will the error make my mesh not converge?

My second issue is that I cannot get my sim to converge, any tips would be appreciated. Here is my config file attached too

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% 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= EULER
%
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 = 0.0
%
%
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= ( FAR )

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, -0.1, 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 0.0
%
ROTATION_RATE= 0.0, 62.44, 0.1

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES

CFL_NUMBER= 0.01
%%
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-16
%%
LINEAR_SOLVER_ITER= 50
%
% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
VENKAT_LIMITER_COEFF= 0.05
LIMITER_ITER= 999999
%
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
CONV_NUM_METHOD_FLOW= JST
%
MUSCL_FLOW= NO
%
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= 1E-8
%%
CONV_STARTITER= 10
%%
CONV_CAUCHY_ELEMS= 200
%%
CONV_CAUCHY_EPS= 1E-6
%%
CONV_FIELD= (LIFT,DRAG)
%%
WINDOW_CAUCHY_CRIT = NO
%%
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= MARK1TALL.su2
%
MESH_FORMAT= SU2
%
MESH_OUT_FILENAME= MESH1_out.su2
%
SOLUTION_FILENAME= restart_flow.csv
%
SOLUTION_ADJ_FILENAME= solution_adj.csv
%
TABULAR_FORMAT= CSV
%
OUTPUT_FILES= (PARAVIEW, SURFACE_PARAVIEW, RESTART_ASCII)
%
CONV_FILENAME= history
%
RESTART_FILENAME= restart_flow.csv
%
RESTART_ADJ_FILENAME= restart_adj.csv
VOLUME_FILENAME= flow
%
VOLUME_ADJ_FILENAME= adjoint
%
VALUE_OBJFUNC_FILENAME= of_eval.csv
%
GRAD_OBJFUNC_FILENAME= of_grad.csv
%
SURFACE_FILENAME= surface_flow
%
SURFACE_ADJ_FILENAME= surface_adjoint
%%
OUTPUT_WRT_FREQ= 100
%
%
WRT_FORCES_BREAKDOWN = YES
%
HISTORY_OUTPUT = (ITER, RMS_RES, AERO_COEFF)
SCREEN_OUTPUT = (INNER_ITER, RMS_DENSITY, LIFT, DRAG, CAUCHY_LIFT,CAUCHY_DRAG)