[ulissesdonis]

Hello

I'm working with condensation phenomena inside nozzles, however, I need to simulate a swirl at the inlet of geometry .
Could someone help me do this in the su2 script?

[bigfootedrockmidget]

Is your geometry axisymmetric except for the rotating component?

The swirl terms are not implemented for 2D axisymmetric flows, so you need to simulate a small 3D wedge and impose the axial, radial and tangential components at the inlet. If you need a more accurate velocity profile at the inlet you can use an input file containing the velocity components.

[ulissesdonis]

Hi Bigfoot

Thanks for answering my question.
I have a 3D geometry (nozzle and axisymmetric) and I need to create a swirl at the Inlet. I attached my script i this message. I have no idea how to generate a swirl. Which part of the script should I put the velocities?

[ulissesdonis]

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: Arina Nozzle %
% Author:Ulisses %
% Institution: University of São Paulo %
% Date: Feb 17th, 2021 %
% File Version 5" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations (EULER, NAVIER_STOKES,
% TNE2_EULER, TNE2_NAVIER_STOKES,
% WAVE_EQUATION, HEAT_EQUATION, LINEAR_ELASTICITY,
% TWO_PHASE_EULER, TWO_PHASE_NAVIER_STOKES, TWO_PHASE_RANS,
% POISSON_EQUATION)
PHYSICAL_PROBLEM= TWO_PHASE_EULER
%
% Specify turbulent model (NONE, SA, SA_NEG, SST)
KIND_TURB_MODEL= NONE
%
% Specify 2phase model (NONE, HILL_RUS)
KIND_2PHASE_MODEL= HILL_RUS
%
% Specify nucleation model (CLASSICAL_THEORY)
KIND_NUCLEATION_MODEL= CLASSICAL_THEORY
%
% Mathematical problem (DIRECT, ADJOINT, LINEARIZED)
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= YES
% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
% Mach number (non-dimensional, based on the free-stream values)
%
MACH_NUMBER= 0.2
%
% Angle of attack (degrees, only for compressible flows)
AoA= 0.0
%
% Free-stream pressure (101325.0 N/m^2 by default, only Euler flows)
FREESTREAM_PRESSURE= 0.25e5
%
% Free-stream temperature (288.15 K by default)
FREESTREAM_TEMPERATURE= 358.0

% Free-stream temperature (1.2886 Kg/m3 by default)
FREESTREAM_DENSITY= 0.152

% Free-stream option to choose if you want to use Density (DENSITY_FS) or Temperature (TEMPERATURE_FS) to initialize the solution
FREESTREAM_OPTION= DENSITY_FS
%
% Free-stream Turbulence Intensity
FREESTREAM_TURBULENCEINTENSITY= 0.05
%
% Free-stream Turbulent to Laminar viscosity ratio
FREESTREAM_TURB2LAMVISCRATIO= 100.0
%
% Reynolds number (non-dimensional, based on the free-stream values)
REYNOLDS_NUMBER= 1.0E5
%
INIT_OPTION= TD_CONDITIONS
%
%SYSTEM_MEASUREMENTS= US
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation
REF_ORIGIN_MOMENT_X= 0.0
REF_ORIGIN_MOMENT_Y= 0.00
REF_ORIGIN_MOMENT_Z= 0.00
%
% Reference length for pitching, rolling, and yawing non-dimensional moment
%REF_LENGTH_MOMENT= 0.6
%
% Reference area for force coefficients (0 implies automatic calculation)
REF_AREA= 0.36
%
% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
REF_DIMENSIONALIZATION= DIMENSIONAL
%
% Reference element length for computing the slope limiter epsilon
REF_ELEM_LENGTH= 0.1

% ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
%
% Different gas model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS)
FLUID_MODEL= PR_GAS
%
% Specify Liquid model (WATER)
KIND_LIQUID_MODEL= WATER
%
% Select model
HEAT_CAPACITY_MODEL = (1791, 0.10689, 5.7611e-4, 1.9978e-7, 0)
%
% Ratio of specific heats (1.4 default and the value is hardcoded
% for the model STANDARD_AIR)
GAMMA_VALUE= 1.33
%
CONSTANT_GAMMA = YES
%
% Specific gas constant (287.058 J/kg*K default and this value is hardcoded
% for the model STANDARD_AIR)
GAS_CONSTANT= 461.51
%
% Critical Temperature (288.15 K by default)
CRITICAL_TEMPERATURE= 647.12
%
% Critical Pressure (101325.0 N/m^2 by default)
CRITICAL_PRESSURE= 22060000.0
%
% Critical Density (1.2886 Kg/m3 by default)
CRITICAL_DENSITY= 322.0
%
% Acentri factor (0.035 (air))
ACENTRIC_FACTOR= 0.3437

% --------------------------- VISCOSITY MODEL ---------------------------------%
%
% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY).
VISCOSITY_MODEL= CONSTANT_VISCOSITY
%
% Molecular Viscosity that would be constant (1.716E-5 by default)
MU_CONSTANT= 11.747e-6
%
% Sutherland Viscosity Ref (1.716E-5 default value for AIR SI)
MU_REF= 11.747e-6
%
% Sutherland Temperature Ref (288.15 K default value for AIR SI)
MU_T_REF= 288.15
%
% Sutherland constant (110.4 default value for AIR SI)
SUTHERLAND_CONSTANT= 110.4

% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
%
% Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL).
CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
%
% Molecular Thermal Conductivity that would be constant (0.0257 by default)
KT_CONSTANT= 23.019e-3

% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
MARKER_SYM= (NONE)

MARKER_EULER=(FLUID_1_1,WALL_NZZL,WALL_SWRL,WALL_S HF1,WALL_SHF2,WALL_SHF3,WALL_SHF4,VAN3S9,WALL_SHF5 ,WALL_SHF6,VAN7S10,VAN7S9,VAN7S8,VAN7S7,VAN7S6,VAN 7S5,VAN7S4,VAN7S3,VAN7S2,VAN7S1,VAN7S11,VAN6S10,VA N6S9,VAN6S8,VAN6S7,VAN6S6,VAN6S5,VAN6S4,VAN6S3,VAN 6S2,VAN6S1,VAN6S11,VAN5S10,VAN5S9,VAN5S8,VAN5S7,VA N5S6,VAN5S5,VAN5S4,VAN5S3,VAN5S2,VAN5S1,VAN5S11,WA LL_SHF7,VAN4S6,VAN4S5,VAN4S4,VAN4S3,VAN4S2,VAN4S1, VAN4S7,VAN4S8,VAN4S9,VAN4S10,VAN4S11,VAN3S8,VAN3S1 0,WALL_SHF8,VAN2S10,VAN3S10VAN2S10,VAN3S11,VAN3S2, VAN3S1,VAN3S3,VAN3S4,VAN3S5,VAN3S6,VAN3S7,WALL_SHF 9,is1S11,VAN2S9,VAN1S1,VAN1S10,VAN2S1,VAN2S2,VAN2S 3,VAN2S4,VAN2S5,VAN2S6,VAN2S7,VAN2S8,VAN1S7,VAN1S8 ,VAN1S9,VAN2S11,VAN1S11,VAN1S5,VAN1S6,VAN1S2,VAN1S 3,VAN1S4)
% Inlet boundary type (TOTAL_CONDITIONS, MASS_FLOW)
INLET_TYPE= TOTAL_CONDITIONS
%
% Inlet boundary marker(s) with the following formats (NONE = no marker)
% Total Conditions: (inlet marker, total temp, total pressure, flow_direction_x,
% flow_direction_y, flow_direction_z, ... ) where flow_direction is
% a unit vector.
% Mass Flow: (inlet marker, density, velocity magnitude, flow_direction_x,
% flow_direction_y, flow_direction_z, ... ) where flow_direction is
% a unit vector.
%MARKER_INLET = (inflow, 358.0, 0.25E+05, 1.0, 0.0, 0.0)
%MARKER_SUPERSONIC_OUTLET= (outflow)
%TOTAL_CONDITIONS_PT
%
MARKER_RIEMANN= (INFLOW, TOTAL_CONDITIONS_PT, 0.25e5, 369, 1.0, 0.0, 0.0, OUTFLOW, STATIC_PRESSURE, 0.040E+05, 0.0, 0.0, 0.0, 0.0)
%
% ------------- COMMON PARAMETERS DEFINING 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= 0.1
% 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 )
%
% Number of total iterations
EXT_ITER= 1000000
%
% Linear solver for the implicit formulation (BCGSTAB, FGMRES)
LINEAR_SOLVER= FGMRES

% Preconditioner of the Krylov linear solver (ILU0, LU_SGS, LINELET, JACOBI)
LINEAR_SOLVER_PREC= ILU0
%
% Min error of the linear solver for the implicit formulation
LINEAR_SOLVER_ERROR= 1E-5
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 600

% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
% Multi-Grid Levels (0 = no multi-grid)
MGLEVEL= 0
%
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
% TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= ROE
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%SPATIAL_ORDER_FLOW= 1ST_ORDER
SPATIAL_ORDER_FLOW= 1ST_ORDER
%
% Slope limiter (VENKATAKRISHNAN, MINMOD)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
% Coefficient for the limiter
LIMITER_COEFF= 1.0
%
% 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

% -------------------- 2-PHASE NUMERICAL METHOD DEFINITION ------------------%
%
% Convective numerical method (SCALAR_UPWIND only)
CONV_NUM_METHOD_2PHASE= SCALAR_UPWIND
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
SPATIAL_ORDER_2PHASE= 1ST_ORDER
%
% Slope limiter (VENKATAKRISHNAN, MINMOD, VAN_ALBADA, SUPERBEE)
SLOPE_LIMITER_2PHASE= VAN_ALBADA
%
% Time discretization (EULER_IMPLICIT)
TIME_DISCRE_2PHASE= EULER_IMPLICIT
%
LIMITER_COEFF_2PHASE = 0
%
% Reduction factor of the CFL coefficient in the 2-phase problem
CFL_REDUCTION_2PHASE= 0.95
%
% Relaxation coefficient
RELAXATION_FACTOR_2PHASE= 0.95


% ------------------------- GRID ADAPTATION STRATEGY --------------------------%
%
% Kind of grid adaptation (NONE, PERIODIC, FULL, FULL_FLOW, GRAD_FLOW, FULL_ADJOINT,
% GRAD_ADJOINT, GRAD_FLOW_ADJ, ROBUST,
% FULL_LINEAR, COMPUTABLE, COMPUTABLE_ROBUST,
% REMAINING, WAKE, SMOOTHING, SUPERSONIC_SHOCK,
% TWOPHASE)
KIND_ADAPT= NONE

% --------------------------- 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= 10
%
% Number of elements to apply the criteria
CAUCHY_ELEMS= 100
%
% Epsilon to control the series convergence
CAUCHY_EPS= 1E-6
%
% 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 (approximately 66k)
MESH_FILENAME= u.su2
%
% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
MESH_FORMAT= SU2
%
% Mesh output file
MESH_OUT_FILENAME= mesh_out.su2
%
% Restart flow input file
SOLUTION_FLOW_FILENAME= restart_flow.dat
%
% Restart 2phase input file
SOLUTION_2PHASE_FILENAME= restart_2phase.dat
%
% Restart adjoint input file
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
% Output file format (PARAVIEW, TECPLOT, STL)
OUTPUT_FORMAT= PARAVIEW
%
% Output file convergence history (w/o extension)
CONV_FILENAME= history
%
% Output file restart flow
RESTART_FLOW_FILENAME= restart_flow.dat
%%
% Output file restart flow
RESTART_2PHASE_FILENAME= restart_2phase.dat
%
% Output file restart adjoint
RESTART_ADJ_FILENAME= restart_adj.dat
%
% Output file flow (w/o extension) variables
VOLUME_FLOW_FILENAME= flow
%
% Output file flow (w/o extension) variables
VOLUME_2PHASE_FILENAME= two_phase_0.25bar
%
% 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
%
% Output residual values in the solution files
WRT_RESIDUALS= YES
%
% Output residual values in the solution files
WRT_LIQUID_PROPS= YES
%
AUTORESET_NEGATIVE_SOL = YES
%
% Writing solution file frequency
WRT_SOL_FREQ= 50
%
% Writing convergence history frequency
WRT_CON_FREQ= 1