propeller_variable_load.cfg

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%                                                                              %
% SU2 configuration file                                                       %
% Case description: Actuator Disk with a semi-infinite spinner                 %
% Author: E. Saetta, L. Russo, R. Tognaccini                                   %
% Institution: Theoretical and Applied Aerodynamic Research Group (TAARG)      %
%              University of Naples Federico II                                %
% Comments: Grid file and propeller data courtesy of Mauro Minervino,          %
%           Centro Italiano Ricerche Aerospaziali (CIRA)                       %
% Date: 07/08/2020                                                             %
% File Version 7.0.7 "Blackbird"                                               %
%                                                                              %
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%----------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION -------------------------%
% Solver type (EULER, NAVIER_STOKES, RANS,
%              INC_EULER, INC_NAVIER_STOKES, INC_RANS
%              FEM_EULER, FEM_NAVIER_STOKES, FEM_RANS, FEM_LES,
%              HEAT_EQUATION_FVM, ELASTICITY)
SOLVER= RANS
%
% Specify turbulence model (NONE, SA, SA_NEG, SST, SA_E, SA_COMP, SA_E_COMP, SST_SUST)
KIND_TURB_MODEL= SA
%
% Turbulence intensity at freestream
FREESTREAM_TURBULENCEINTENSITY=0.01
%
% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT, DISCRETE_ADJOINT)
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= NO
%
% System of measurements (SI, US)
% International system of units (SI): ( meters, kilograms, Kelvins,
%                                       Newtons = kg m/s^2, Pascals = N/m^2, 
%                                       Density = kg/m^3, Speed = m/s,
%                                       Equiv. Area = m^2 )
SYSTEM_MEASUREMENTS= SI
% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.55996
%
% Angle of attack (degrees, only for compressible flows)
AOA= 0.0
%
% Side-slip angle (degrees, only for compressible flows)
SIDESLIP_ANGLE= 0.0
%
% Reynolds number (non-dimensional, based on the free-stream values)
REYNOLDS_NUMBER= 3.65E7
%
% Reynolds length (1 m, 1 inch by default)
REYNOLDS_LENGTH= 5.0292
%
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
% Reference origin for moment computation (m or in)
REF_ORIGIN_MOMENT_X = 0.0
REF_ORIGIN_MOMENT_Y = 0.0
REF_ORIGIN_MOMENT_Z = 0.0
%
% Reference length for moment non-dimensional coefficients (m or in)
REF_LENGTH= 1.0
%
% Reference area for non-dimensional force coefficients (0 implies automatic
% calculation) (m^2 or in^2)
REF_AREA= 19.8649
%
% Compressible flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
%                                           FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
REF_DIMENSIONALIZATION= DIMENSIONAL
%
% --------------- ENGINE AND ACTUATOR DISK SIMULATION -------------------------%
% Highlite area to compute MFR (1 in by default)
HIGHLITE_AREA= 19.8649
%
% Engine nu factor (SA model).
ENGINE_NU_FACTOR= 0.0
%
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
ACTDISK_DOUBLE_SURFACE = YES
%
% Actuator disk boundary type (VARIABLE_LOAD, VARIABLES_JUMP, BC_THRUST,
%                              DRAG_MINUS_THRUST)
ACTDISK_TYPE= VARIABLE_LOAD
%
% Actuator disk data input file name
ACTDISK_FILENAME= ActuatorDisk.dat
%
% Actuator disk boundary marker(s) with the following formats (NONE = no marker)
% Variable Load: (inlet face marker, outlet face marker,
%                 0.0, 0.0, 0.0, 0.0, 0.0, 0.0) Markers only effectively used.
MARKER_ACTDISK = ( DISK, DISK_BACK, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0 )
%
% Far-field boundary marker(s) (NONE = no marker)
MARKER_FAR= ( FF )
%
% Outlet boundary marker(s) (NONE = no marker)
% Compressible: ( outlet marker, back pressure (static thermodynamic), ... )
MARKER_OUTLET = ( OUT , 56370.2)
%
% Navier-Stokes (no-slip), constant heat flux wall  marker(s) (NONE = no marker)
% Format: ( marker name, constant heat flux (J/m^2), ... )
MARKER_HEATFLUX = (SPINNER, 0.0)
%
% ------------------------ SURFACES IDENTIFICATION ----------------------------%
% Marker(s) of the surface in the surface flow solution file
MARKER_PLOTTING = ( DISK, DISK_BACK, SPINNER )
%
% Marker(s) of the surface where the non-dimensional coefficients are evaluated.
MARKER_MONITORING = ( DISK, DISK_BACK, SPINNER )
%
% Marker(s) of the surface that is going to be analyzed in detail (massflow, average pressure, distortion, etc)
MARKER_ANALYZE = ( DISK, DISK_BACK )
%
% Method to compute the average value in MARKER_ANALYZE (AREA, MASSFLUX).
MARKER_ANALYZE_AVERAGE = MASSFLUX
%
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= GREEN_GAUSS
%
% CFL number (initial value for the adaptive CFL number)
CFL_NUMBER= 20.0
%
% Adaptive CFL number (NO, YES)
CFL_ADAPT= NO
%
% Objective function in gradient evaluation   (DRAG, LIFT, SIDEFORCE, MOMENT_X,
%                                             MOMENT_Y, MOMENT_Z, EFFICIENCY, BUFFET,
%                                             EQUIVALENT_AREA, NEARFIELD_PRESSURE,
%                                             FORCE_X, FORCE_Y, FORCE_Z, THRUST,
%                                             TORQUE, TOTAL_HEATFLUX,
%                                             MAXIMUM_HEATFLUX, INVERSE_DESIGN_PRESSURE,
%                                             INVERSE_DESIGN_HEATFLUX, SURFACE_TOTAL_PRESSURE, 
%                                             SURFACE_MASSFLOW, SURFACE_STATIC_PRESSURE, SURFACE_MACH)
% For a weighted sum of objectives: separate by commas, add OBJECTIVE_WEIGHT and MARKER_MONITORING in matching order.
OBJECTIVE_FUNCTION= DRAG
%
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
% Linear solver or smoother for implicit formulations:
% BCGSTAB, FGMRES, RESTARTED_FGMRES, CONJUGATE_GRADIENT (self-adjoint problems only), SMOOTHER.
LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver or type of smoother (ILU, LU_SGS, LINELET, JACOBI)
LINEAR_SOLVER_PREC= ILU
%
% Minimum error of the linear solver for implicit formulations
LINEAR_SOLVER_ERROR= 1E-12
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 3
%
% Number of elements to apply the criteria
CONV_CAUCHY_ELEMS= 1000
%
% Epsilon to control the series convergence
CONV_CAUCHY_EPS= 1E-10
%
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, AUSMPLUSUP,
%                              AUSMPLUSUP2, HLLC, TURKEL_PREC, MSW, FDS, SLAU, SLAU2)
CONV_NUM_METHOD_FLOW= JST
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_FLOW= EULER_IMPLICIT
%
% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
% Convective numerical method (SCALAR_UPWIND)
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
%
% Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations.
%           Required for 2nd order upwind schemes (NO, YES)
MUSCL_TURB= NO
%
% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,
%                BARTH_JESPERSEN, VAN_ALBADA_EDGE)
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
%
% Time discretization (EULER_IMPLICIT)
TIME_DISCRE_TURB= EULER_IMPLICIT
%
% --------------------------- CONVERGENCE PARAMETERS --------------------------%
% Maximum number of iterations
ITER= 1500
%
% Min value of the residual (log10 of the residual)
CONV_RESIDUAL_MINVAL= -8
%
% Start convergence criteria at iteration number
CONV_STARTITER= 10
%
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
% Mesh input file
MESH_FILENAME= propeller_variable_load.su2
%
% Mesh input file format (SU2, CGNS)
MESH_FORMAT= SU2
%
% Mesh output file
MESH_OUT_FILENAME= mesh_out.su2
%
% Restart flow input file
SOLUTION_FILENAME= restart_flow
%
% Output tabular file format (TECPLOT, CSV)
TABULAR_FORMAT= TECPLOT
%
% Output file convergence history (w/o extension)
CONV_FILENAME= history
%
% Write the forces breakdown file option (NO, YES)
WRT_FORCES_BREAKDOWN= YES
%
% Output file with the forces breakdown
BREAKDOWN_FILENAME= forces_breakdown.dat
%
% Output file restart flow
RESTART_FILENAME= restart_flow
%
% Output file flow (w/o extension) variables
VOLUME_FILENAME= flow
%
% Output file surface flow coefficient (w/o extension)
SURFACE_FILENAME= surface_flow
%
%
%
%
% Screen output fields
SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_NU_TILDE, LIFT, DRAG)