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* ThermoData branch Turboprop and turbofan exit condition calculation module added Co-authored-by: Francesco-Marcucci <[email protected]>
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| %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
| % % | ||
| % SU2 configuration file % | ||
| % Case description: VKI turbine % | ||
| % Author: Francisco Palacios, Thomas D. Economon % | ||
| % Institution: Stanford University % | ||
| % Date: Feb 18th, 2013 % | ||
| % File Version 8.0.0 "Harrier" % | ||
| % % | ||
| %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
|
|
||
| % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% | ||
| % | ||
| SOLVER= RANS | ||
| % | ||
| KIND_TURB_MODEL= SA | ||
| % | ||
| MATH_PROBLEM= DIRECT | ||
| % | ||
| RESTART_SOL= NO | ||
| % | ||
| SYSTEM_MEASUREMENTS= SI | ||
|
|
||
| % -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% | ||
| % | ||
| MACH_NUMBER= 0.3 | ||
| % | ||
| AOA= 0.0 | ||
| % | ||
| FREESTREAM_PRESSURE= 1.013E5 | ||
| % | ||
| FREESTREAM_OPTION= DENSITY_FS | ||
| % | ||
| FREESTREAM_DENSITY = 1.255 | ||
| % | ||
| FREESTREAM_TEMPERATURE =288.15 | ||
| % | ||
| REYNOLDS_NUMBER= 4E6 | ||
| % | ||
| REYNOLDS_LENGTH= 1.0 | ||
|
|
||
| % ---------------------- REFERENCE VALUE DEFINITION ---------------------------% | ||
| % | ||
| REF_ORIGIN_MOMENT_X = 0.00 | ||
| % | ||
| REF_ORIGIN_MOMENT_Y = 0.00 | ||
| % | ||
| REF_ORIGIN_MOMENT_Z = 0.00 | ||
| % | ||
| REF_LENGTH= 45.0 | ||
| % | ||
| REF_AREA= 1 | ||
| % Compressible flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE, | ||
| % FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE) | ||
| REF_DIMENSIONALIZATION= FREESTREAM_PRESS_EQ_ONE | ||
| % | ||
| % ----------------------- BOUNDARY CONDITION DEFINITION -----------------------% | ||
| % | ||
| MARKER_HEATFLUX = (S4CreatedbyGmsh, 0.0) | ||
| % | ||
| MARKER_FAR= (S3Farfield) | ||
| % | ||
| %MARKER_SYM =() | ||
| % | ||
| % ------------------------ SURFACES IDENTIFICATION ----------------------------% | ||
| % | ||
| % Marker(s) of the surface to be plotted or designed | ||
| MARKER_PLOTTING= (S4CreatedbyGmsh) | ||
| % | ||
| % Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated | ||
| MARKER_MONITORING= (S4CreatedbyGmsh) | ||
|
|
||
| % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% | ||
| % | ||
| NUM_METHOD_GRAD= GREEN_GAUSS | ||
| % | ||
| CFL_NUMBER= 1 | ||
| % | ||
| CFL_ADAPT= NO | ||
| % | ||
| CFL_ADAPT_PARAM= ( 0.5, 1, 1.0, 100.0 ) | ||
| % | ||
| ITER = 5000 | ||
|
|
||
| % 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 | ||
| % -------------------------- MULTIGRID PARAMETERS -----------------------------% | ||
| % | ||
| % Multi-Grid Levels (0 = no multi-grid) | ||
| MGLEVEL = 3 | ||
| % | ||
| % Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE) | ||
| MGCYCLE = W_CYCLE | ||
| % | ||
| % Multi-Grid PreSmoothing Level | ||
| MG_PRE_SMOOTH = ( 1.0, 2.0, 3.0, 3.0 ) | ||
| % | ||
| % Multi-Grid PostSmoothing Level | ||
| MG_POST_SMOOTH = ( 0.0, 0.0, 0.0, 0.0 ) | ||
| % | ||
| % Jacobi implicit smoothing of the correction | ||
| MG_CORRECTION_SMOOTH = ( 0.0, 0.0, 0.0, 0.0 ) | ||
| % | ||
| % Damping factor for the residual restriction | ||
| MG_DAMP_RESTRICTION = 0.9 | ||
| % | ||
| % Damping factor for the correction prolongation | ||
| MG_DAMP_PROLONGATION = 0.9 | ||
| % --------------------------- CONVERGENCE PARAMETERS --------------------------% | ||
| % | ||
| % Min value of the residual (log10 of the residual) | ||
| CONV_RESIDUAL_MINVAL= -12 | ||
| % | ||
| % Start convergence criteria at iteration number | ||
| CONV_STARTITER= 10 | ||
| % | ||
|
|
||
| % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% | ||
| % | ||
| MESH_FILENAME= labair_penta.su2 | ||
| % | ||
| MESH_FORMAT= SU2 | ||
| % | ||
| MESH_OUT_FILENAME= mesh_out.su2 | ||
| % | ||
| SOLUTION_FILENAME= solution_flow.dat | ||
| % | ||
| HISTORY_OUTPUT = (INNER_ITER, RMS_RES, AERO_COEFF) | ||
| % | ||
| TABULAR_FORMAT= CSV | ||
| % | ||
| CONV_FILENAME= history | ||
| % | ||
| RESTART_FILENAME= restart_flow.dat | ||
| % | ||
| RESTART_ADJ_FILENAME= restart_adj.dat | ||
| % | ||
| VOLUME_FILENAME= flow | ||
| % | ||
| SURFACE_FILENAME= surface_flow | ||
| % | ||
| OUTPUT_WRT_FREQ= 100 | ||
| % | ||
| BREAKDOWN_FILENAME = forces_breakdown_def.dat | ||
| % | ||
| WRT_FORCES_BREAKDOWN = YES | ||
| % | ||
| SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG) |
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