con_rae2822_air_0.cfg

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%                                                                              %
% SU2 configuration file                                                       %
% Case description: Transonic Turbulent flow over a RAE2822 Airfoil            %
% Author: Susmit Joshi		                                               %
% Institution: Virginia Tech 			                               %
% Date: 12/31/2024		                                               %
% File Version 7.1.1/8.0		                                       %
%                                                                              %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations (EULER, NAVIER_STOKES,
%                               WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
%                               POISSON_EQUATION)
SOLVER= RANS
%
% Kind of turbulent model (NONE, SA, SA_NEG, SST) 
KIND_TURB_MODEL = SA
%
% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= NO
%
SYSTEM_MEASUREMENTS= SI
%
AXISYMMETRIC= NO
%------------------------------------------------------------------------------%

% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.8
%
% Angle of attack (degrees)
AOA= 0.0
%
% Side-slip angle (degrees)
SIDESLIP_ANGLE= 0.0
%
% Init option to choose between Reynolds (default) or thermodynamics quantities
% for initializing the solution (REYNOLDS, TD_CONDITIONS)
INIT_OPTION= REYNOLDS
%
% Free-stream option to choose between density and temperature (default) for
% initializing the solution (TEMPERATURE_FS, DENSITY_FS)
FREESTREAM_OPTION= TEMPERATURE_FS
%
% Free-stream pressure (101325.0 N/m^2 by default, only Euler flows)  
FREESTREAM_PRESSURE= 101325.0
%
% Free-stream temperature (288.15 K by default, 254 for RAM C-II)
FREESTREAM_TEMPERATURE= 288.15
%
% Reynolds number (non-dimensional, based on the free-stream values)
REYNOLDS_NUMBER= 1.8464E+07
%
% Reynolds length (1 m, 1 inch by default)
REYNOLDS_LENGTH= 1.0
%
%------------------------------------------------------------------------------%

% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation (m or in)
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference length for moment non-dimensional coefficients (m or in)
REF_LENGTH= 1
%
% Reference area for non-dimensional force coefficients (0 implies automatic
% calculation) (m^2 or in^2)
% REF_AREA= 2.0321
REF_AREA= 0.2
%
% Aircraft semi-span (0 implies automatic calculation) (m or in)
SEMI_SPAN= 0.2
%------------------------------------------------------------------------------%

% ---- NONEQUILIBRIUM GAS, IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
%
% Fluid model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS,
%              CONSTANT_DENSITY, INC_IDEAL_GAS, INC_IDEAL_GAS_POLY, MUTATIONPP, SU2_NONEQ)
FLUID_MODEL= STANDARD_AIR
%------------------------------------------------------------------------------%

% --------------------------- VISCOSITY MODEL ---------------------------------%
%
% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY, POLYNOMIAL_VISCOSITY).
VISCOSITY_MODEL= SUTHERLAND
%
% Molecular Viscosity that would be constant (1.716E-5 by default)
MU_CONSTANT= 1.716E-5
%
% Sutherland Viscosity Ref (1.716E-5 default value for AIR SI)
MU_REF= 1.716E-5
%
% Sutherland Temperature Ref (273.15 K default value for AIR SI)
MU_T_REF= 273.15
%
% Sutherland constant (110.4 default value for AIR SI)
SUTHERLAND_CONSTANT= 110.4
%------------------------------------------------------------------------------%

% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
%
% Laminar Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL,
% POLYNOMIAL_CONDUCTIVITY).
CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
%
% Laminar Prandtl number (0.72 (air), only for CONSTANT_PRANDTL)
PRANDTL_LAM= 0.72
%
% Turbulent Prandtl number (0.9 (air), only for CONSTANT_PRANDTL)
PRANDTL_TURB= 0.9
%------------------------------------------------------------------------------%

%--------------------- WALL FUNCTION DEFINITION ------------------------------%
%
% The von Karman constant, constant below only affects the standard wall function model
WALLMODEL_KAPPA= 0.41
%
% The wall function model constant B
WALLMODEL_B= 5.5
%
% The y+ value below which the wall function is switched off and we resolve the wall
WALLMODEL_MINYPLUS= 5.0
%
% [Expert] Max Newton iterations used for the standard wall function
% WALLMODEL_MAXITER= 200
%
% [Expert] Relaxation factor for the Newton iterations of the standard wall function
% WALLMODEL_RELFAC= 0.5
%------------------------------------------------------------------------------%

% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
% Navier-Stokes wall boundary marker(s) (NONE = no marker)
MARKER_HEATFLUX= (AIRFOIL, 0.0)
%
MARKER_FAR= (FARFIELD)
%
MARKER_SYM= (SYMMETRY)
%
% Inlet boundary marker(s)
% Format: ( Inlet marker, total temp, total press, flow_direction_x, flow_direction_y, flow_direction_z, ...)
MARKER_INLET= (INLET, 323.3516, 1.6391E+05, 1.0, 0.0, 0.0)
%
% Outlet boundary marker(s)
% Format: ( Outlet Marker, back pressure, ...)
MARKER_OUTLET= (OUTLET, 101325)
%
% Marker(s) of the surface to be plotted or designed
MARKER_PLOTTING= (AIRFOIL)
%
% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
MARKER_MONITORING= (AIRFOIL)
%------------------------------------------------------------------------------%

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
% Numerical method for spatial gradients (GREEN_GAUSS, LEAST_SQUARES, 
%                                         WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
%
% Courant-Friedrichs-Lewy condition of the finest grid
CFL_NUMBER= 100.0
%
% Adaptive CFL number (NO, YES)
CFL_ADAPT= YES
%
% Parameters of the adaptive CFL number (factor-down, factor-up, CFL min value,
%                                        CFL max value, acceptable linear solver convergence)
% Local CFL increases by factor-up until max if the solution rate of change is not limited,
% and acceptable linear convergence is achieved. It is reduced if rate is limited, or if there
% is not enough linear convergence, or if the nonlinear residuals are stagnant and oscillatory.
% It is reset back to min when linear solvers diverge, or if nonlinear residuals increase too much.
CFL_ADAPT_PARAM= ( 0.1, 2.0, 1, 1e4 )
%
% Number of total iterations
ITER= 100000
%
% Linear solver for the implicit formulation (BCGSTAB, FGMRES)
LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS)
LINEAR_SOLVER_PREC= ILU 
%
% Min error of the linear solver for the implicit formulation
LINEAR_SOLVER_ERROR= 1E-10
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 10
% 
% Runge-Kutta alpha coefficients
RK_ALPHA_COEFF= (0.66667, 0.66667, 1.0) 
%------------------------------------------------------------------------%

% ------------------ FLOW NUMERICAL METHOD DEFINITION -------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
%                              TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= JST
%
% 2nd and 4th order artificial dissipation coefficients for JST method (0.5, 0.02 by default)
JST_SENSOR_COEFF= (0.5, 0.02)
%
MUSCL_FLOW= NO
%
% Slope limiter (VENKATAKRISHNAN, MINMOD)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
% Coefficient for the Venkat's limiter (upwind scheme). A larger values decrease
%             the extent of limiting, values approaching zero cause
%             lower-order approximation to the solution (0.05 by default)
VENKAT_LIMITER_COEFF= 0.05
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_FLOW= EULER_IMPLICIT
%
% Reference coefficient (sensitivity) for detecting sharp edges
REF_SHARP_EDGES= 3.0
%------------------------------------------------------------------------------%

% ------------------ TURBULENT NUMERICAL METHOD DEFINITION --------------------%
%
% Convective numerical method 
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
%
MUSCL_TURB= NO
%
% Slope limiter (VENKATAKRISHNAN, MINMOD)
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_TURB= EULER_IMPLICIT
%------------------------------------------------------------------------------%


% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
% Convergence criteria (CAUCHY, RESIDUAL)
%
% CONV_CRITERIA= CAUCHY
%
CONV_FIELD = RMS_DENSITY
%
% Min value of the residual (log10 of the residual)
CONV_RESIDUAL_MINVAL= -14
%
% Start convergence criteria at iteration number
CONV_STARTITER= 10
%
% Number of elements to apply the criteria
CONV_CAUCHY_ELEMS= 100
%
% Epsilon to control the series convergence
CONV_CAUCHY_EPS= 1E-6
%------------------------------------------------------------------------------%

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
% Volume output fields/groups (use 'SU2_CFD -d <config_file>' to view list of available fields)
VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, RESIDUAL, TIMESTEP, MESH_QUALITY)
%
% Screen output fields (use 'SU2_CFD -d <config_file>' to view list of available fields)
SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, WALL_TIME)
%
% History output groups (use 'SU2_CFD -d <config_file>' to view list of available fields)
HISTORY_OUTPUT= (ITER, RMS_RES, AERO_COEFF)
%
% Mesh input file
MESH_FILENAME= rae2822-127k.su2
%
% Mesh input file format (SU2, CGNS)
MESH_FORMAT= SU2
%
% Restart flow input file
SOLUTION_FILENAME= sol_rae2822_air_0.csv  
%
% Output file format (CSV, TECPLOT)
TABULAR_FORMAT= TECPLOT 
%
% Output file convergence history (w/o extension) 
CONV_FILENAME= hist_rae2822_air_0
%
% Output file restart flow
RESTART_FILENAME= rest_rae2822_air_0.csv
%
% Read binary restart files (looks for .dat restart files) (YES, NO)
READ_BINARY_RESTART= NO
%
% Output file flow (w/o extension) variables
VOLUME_FILENAME= vol_rae2822_air_0
%
% Output file surface flow coefficient (w/o extension)
SURFACE_FILENAME= sur_rae2822_air_0   
%
OUTPUT_WRT_FREQ= 100000
%
% Files to output 
% Possible formats : (TECPLOT, SURFACE_TECPLOT,
%  CSV, SURFACE_CSV, PARAVIEW, SURFACE_PARAVIEW, 
%  MESH, RESTART_ASCII, CGNS, STL)
% default : (RESTART, PARAVIEW, SURFACE_PARAVIEW)
OUTPUT_FILES= (RESTART_ASCII, CSV, SURFACE_CSV)
%------------------------------------------------------------------------------%