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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 | ||
|
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# More than one propeller data can be appended here. |
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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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