[Bakhshi]

Hello

I am trying to do simulation of a rotor in SU2, using rotating frame reference. However the solution is diverging. I am new to SU2, and unable to figure out the problem in my configuration file. The simulation is converging for the same solver if the rotor is not rotating. I am attaching the configuration file for the reference.


%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: Caradonna & Tung rotor in hover (still air) %
% Author: Thomas D. Economon %
% Institution: Stanford University %
% Date: 2020.05.24 %
% File Version 8.0.0 "Harrier" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
SOLVER= RANS
KIND_TURB_MODEL= SA
MATH_PROBLEM= DIRECT
RESTART_SOL= NO

% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
%
MACH_NUMBER= 0.00
AOA= 90.0
SIDESLIP_ANGLE= 90.0
%FREESTREAM_PRESSURE= 101325.0
FREESTREAM_TEMPERATURE= 288.15
REYNOLDS_NUMBER= 0.94778E6
REYNOLDS_LENGTH= 0.114

% --------------------------- VISCOSITY MODEL ---------------------------------%
%
VISCOSITY_MODEL= SUTHERLAND
MU_CONSTANT= 1.716E-5
MU_REF= 1.716E-5
MU_T_REF= 273.15
SUTHERLAND_CONSTANT= 110.4

% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
REF_ORIGIN_MOMENT_X = 0.00
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
REF_LENGTH= 0.114
REF_AREA= 00.0

% ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
%
GRID_MOVEMENT= ROTATING_FRAME
MACH_MOTION= 0.174
MOTION_ORIGIN= 0.0 0.0 0.0
ROTATION_RATE = 0.0 -523.598775 0.0
% 1250 RPM -> 130.89969389957471
% 2500 RPM -> 261.79938779914943

% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
MARKER_HEATFLUX= ( ROTOR, 0.0 )
MARKER_FAR= ( FARFIELD )
MARKER_PLOTTING= ( ROTOR )
MARKER_MONITORING= ( ROTOR )

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
NUM_METHOD_GRAD= GREEN_GAUSS
CFL_NUMBER= 1000
CFL_ADAPT= NO
CFL_ADAPT_PARAM= ( 0.1, 2.0, 15, 1e6 )
RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
ITER= 99999

% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
LINEAR_SOLVER= FGMRES
LINEAR_SOLVER_PREC= ILU
LINEAR_SOLVER_ERROR= 1E-10
LINEAR_SOLVER_ITER= 10

% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
MGLEVEL= 0
MGCYCLE= W_CYCLE
MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
MG_POST_SMOOTH= ( 0, 0, 0, 0 )
MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
MG_DAMP_RESTRICTION= 0.9
MG_DAMP_PROLONGATION= 0.9

% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
CONV_NUM_METHOD_FLOW= JST
MUSCL_FLOW = NO
JST_SENSOR_COEFF= ( 0.5, 0.02 )
TIME_DISCRE_FLOW= EULER_IMPLICIT

% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
%
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
MUSCL_TURB= NO
SLOPE_LIMITER_TURB= NONE
TIME_DISCRE_TURB= EULER_IMPLICIT

% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
CONV_FIELD= RMS_DENSITY
CONV_RESIDUAL_MINVAL= -6
CONV_STARTITER= 10
CONV_CAUCHY_ELEMS= 100
CONV_CAUCHY_EPS= 1E-10

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
MESH_FILENAME= rotor3.su2
MESH_FORMAT= SU2
MESH_OUT_FILENAME= mesh_caradonna_tung_periodic.su2
SOLUTION_FILENAME= solution_flow.dat
SOLUTION_ADJ_FILENAME= solution_adj.dat
TABULAR_FORMAT= CSV
CONV_FILENAME= history
RESTART_FILENAME= restart_flow.dat
RESTART_ADJ_FILENAME= restart_adj.dat
VOLUME_FILENAME= flow
VOLUME_ADJ_FILENAME= adjoint
GRAD_OBJFUNC_FILENAME= of_grad.dat
SURFACE_FILENAME= surface_flow
SURFACE_ADJ_FILENAME= surface_adjoint
OUTPUT_WRT_FREQ= 100
SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_DENSITY, LIFT, DRAG, AVG_CFL)


The error on the terminal is
Error in "void CSolver::SetResidual_RMS(const CGeometry*, const CConfig*)":
-------------------------------------------------------------------------
SU2 has diverged (NaN detected).
------------------------------ Error Exit -------------------------------

Thank you for the help.