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pcarruscagpcarruscag
authoredJan 20, 2021
Merge pull request #8 from su2code/develop
Update master
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v8.1.0v7.1.0
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‎compressible_flow/ActuatorDisk_VariableLoad/ActuatorDisk.dat

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

‎compressible_flow/ActuatorDisk_VariableLoad/propeller_variable_load.cfg

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

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