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Merge pull request #8 from su2code/develop
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pcarruscag authored Jan 20, 2021
2 parents 36d1a0f + 2562249 commit a3e5ec9
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54 changes: 54 additions & 0 deletions compressible_flow/ActuatorDisk_VariableLoad/ActuatorDisk.dat
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# TEST CASE PROPELLER DATA.
# ADV_RATIO defined as Vinf/(nD) where n: propeller rounds per second, D: propeller diameter.
# "Renard" definition of propeller coefficients:
# reference force = rho*n^2*D^4, reference power = rho*n^3*D^5.
# Propeller center in grid coordinates.
# Propeller axis versor pointing backward.
# Total thrust coefficient CT = 0.15.
# ----------------------------------------------------------------------------------------------- #
MARKER_ACTDISK= DISK DISK_BACK
CENTER= 0.0 0.0 0.0
AXIS= 1.0 0.0 0.0
RADIUS= 2.5146
ADV_RATIO= 2.81487
NROW= 37
# rs=r/R dCT/drs dCP/drs dCR/drs
0.2031 0.020066 0.0890674 0.0
0.2235 0.019963 0.0932674 0.0
0.2439 0.021707 0.0982980 0.0
0.2644 0.024667 0.1064153 0.0
0.2848 0.029147 0.1189045 0.0
0.3257 0.043674 0.1588513 0.0
0.3461 0.053380 0.1849900 0.0
0.3665 0.064327 0.2145367 0.0
0.3870 0.076521 0.2471873 0.0
0.4278 0.103679 0.3203392 0.0
0.4483 0.118918 0.3609085 0.0
0.4687 0.135619 0.4051864 0.0
0.4891 0.152986 0.4518863 0.0
0.5096 0.171453 0.5011266 0.0
0.5300 0.190755 0.5528521 0.0
0.5504 0.211062 0.6072281 0.0
0.5709 0.231313 0.6620508 0.0
0.5913 0.251252 0.7161404 0.0
0.6117 0.271376 0.7700722 0.0
0.6322 0.290980 0.8219708 0.0
0.6526 0.309848 0.8715231 0.0
0.6730 0.328502 0.9202496 0.0
0.6935 0.346774 0.9681596 0.0
0.7139 0.364895 1.0156277 0.0
0.7343 0.381991 1.0603740 0.0
0.7548 0.398417 1.1036331 0.0
0.7752 0.413550 1.1442054 0.0
0.7956 0.427447 1.1820164 0.0
0.8161 0.440093 1.2163819 0.0
0.8365 0.451007 1.2453084 0.0
0.8569 0.460535 1.2682212 0.0
0.8774 0.467765 1.2823500 0.0
0.8978 0.471296 1.2839416 0.0
0.9182 0.470303 1.2701343 0.0
0.9387 0.460921 1.2317719 0.0
0.9591 0.434937 1.1470356 0.0
0.9795 0.377288 0.9746048 0.0

# More than one propeller data can be appended here.
234 changes: 234 additions & 0 deletions compressible_flow/ActuatorDisk_VariableLoad/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" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

%----------- 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
%
% Convergence criteria (CAUCHY, RESIDUAL)
CONV_CRITERIA= RESIDUAL
%
% 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.dat
%
% 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.dat
%
% 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)
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