diff --git a/Common/include/CConfig.hpp b/Common/include/CConfig.hpp index 7c07dd8a0cc..d5d118aa1de 100644 --- a/Common/include/CConfig.hpp +++ b/Common/include/CConfig.hpp @@ -932,6 +932,7 @@ class CConfig { Pressure_Thermodynamic, /*!< \brief Thermodynamic pressure of the fluid. */ Temperature_FreeStream, /*!< \brief Total temperature of the fluid. */ Temperature_ve_FreeStream; /*!< \brief Total vibrational-electronic temperature of the fluid. */ + bool out2in_mdot_engine; /*!< \brief Flag to use engine outlet mass flow as engine inlet mass flow. */ unsigned short wallModel_MaxIter; /*!< \brief maximum number of iterations for the Newton method for the wall model */ su2double wallModel_Kappa, /*!< \brief von Karman constant kappa for turbulence wall modeling */ wallModel_B, /*!< \brief constant B for turbulence wall modeling */ @@ -2118,6 +2119,12 @@ class CConfig { */ su2double GetNuFactor_Engine(void) const { return NuFactor_Engine; } + /*! + * \brief Get the flag to use exhaust mass flow as inlet mass flow. + * \return TRUE if exhaust mass flow is used as inlet mass flow. + */ + bool GetExhaustToInlet_Engine(void) const { return out2in_mdot_engine; } + /*! * \brief Get the value of the non-dimensionalized actuator disk turbulence intensity. * \return Non-dimensionalized actuator disk intensity. diff --git a/Common/src/CConfig.cpp b/Common/src/CConfig.cpp index 18884a52a35..79fe6d6aab1 100644 --- a/Common/src/CConfig.cpp +++ b/Common/src/CConfig.cpp @@ -1793,6 +1793,8 @@ void CConfig::SetConfig_Options() { addEnumOption("ENGINE_INFLOW_TYPE", Kind_Engine_Inflow, Engine_Inflow_Map, FAN_FACE_MACH); /* DESCRIPTION: Evaluate a problem with engines */ addBoolOption("ENGINE", Engine, false); + /* DESCRIPTION: Use exhaust mass flow as inlet mass flow. */ + addBoolOption("ENGINE_EXHAUST_TO_INLET", out2in_mdot_engine, false); /* DESCRIPTION: Sharpness coefficient for the buffet sensor */ addDoubleOption("BUFFET_K", Buffet_k, 10.0); diff --git a/SU2_CFD/src/solvers/CEulerSolver.cpp b/SU2_CFD/src/solvers/CEulerSolver.cpp index 6ac5b7a162c..3f8d642e9c6 100644 --- a/SU2_CFD/src/solvers/CEulerSolver.cpp +++ b/SU2_CFD/src/solvers/CEulerSolver.cpp @@ -7622,6 +7622,17 @@ void CEulerSolver::BC_Engine_Inflow(CGeometry *geometry, CSolver **solver_contai Target_Inflow_MassFlow = config->GetEngineInflow_Target(Marker_Tag) / (config->GetDensity_Ref() * config->GetVelocity_Ref()); + if (config->GetExhaustToInlet_Engine()) { + su2double Outlet_MF = 0.0; + unsigned short nMarker_Global = config->GetnMarker_CfgFile(); + for (unsigned short iMarker_Global = 0; iMarker_Global < nMarker_Global; iMarker_Global++) { + if (config->GetMarker_CfgFile_KindBC(config->GetMarker_CfgFile_TagBound(iMarker_Global)) == ENGINE_EXHAUST) { + Outlet_MF = Outlet_MF + config->GetExhaust_MassFlow(config->GetMarker_CfgFile_TagBound(iMarker_Global)); + } + } + Target_Inflow_MassFlow = Outlet_MF; + } + if (config->GetSystemMeasurements() == US) Target_Inflow_MassFlow /= 32.174; if (Engine_HalfModel) Target_Inflow_MassFlow /= 2.0; diff --git a/TestCases/turbofan_MFR_coupling/MFR_coupling.cfg b/TestCases/turbofan_MFR_coupling/MFR_coupling.cfg new file mode 100644 index 00000000000..06517496d82 --- /dev/null +++ b/TestCases/turbofan_MFR_coupling/MFR_coupling.cfg @@ -0,0 +1,685 @@ +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% +% % +% SU2 configuration file % +% Case description: _________________________________________________________ % +% Author: ___________________________________________________________________ % +% Institution: ______________________________________________________________ % +% Date: __________ % +% File Version 7.2.0 "Blackbird" % +% % +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% + +% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% +% +% Solver type (EULER, NAVIER_STOKES, RANS, +% INC_EULER, INC_NAVIER_STOKES, INC_RANS, +% NEMO_EULER, NEMO_NAVIER_STOKES, +% 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 +% +% Specify versions/corrections of the SST model (V2003m, V1994m, VORTICITY, KATO_LAUNDER, UQ, SUSTAINING) +SST_OPTIONS= V2003m +% +% Specify versions/corrections of the SA model (NEGATIVE, EDWARDS, WITHFT2, QCR2000, COMPRESSIBILITY, ROTATION, BCM, EXPERIMENTAL) +SA_OPTIONS= NEGATIVE, WITHFT2 +% +% Specify subgrid scale model(NONE, IMPLICIT_LES, SMAGORINSKY, WALE, VREMAN) +KIND_SGS_MODEL= NONE +% +% Specify the verification solution(NO_VERIFICATION_SOLUTION, INVISCID_VORTEX, +% RINGLEB, NS_UNIT_QUAD, TAYLOR_GREEN_VORTEX, +% MMS_NS_UNIT_QUAD, MMS_NS_UNIT_QUAD_WALL_BC, +% MMS_NS_TWO_HALF_CIRCLES, MMS_NS_TWO_HALF_SPHERES, +% MMS_INC_EULER, MMS_INC_NS, INC_TAYLOR_GREEN_VORTEX, +% USER_DEFINED_SOLUTION) +KIND_VERIFICATION_SOLUTION= NO_VERIFICATION_SOLUTION +% +% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT, DISCRETE_ADJOINT) +MATH_PROBLEM= DIRECT +% +% Axisymmetric simulation, only compressible flows (NO, YES) +AXISYMMETRIC= NO +% +% Restart solution (NO, YES) +RESTART_SOL= NO +% +% Discard the data storaged in the solution and geometry files +% e.g. AOA, dCL/dAoA, dCD/dCL, iter, etc. +% Note that AoA in the solution and geometry files is critical +% to aero design using AoA as a variable. (NO, YES) +DISCARD_INFILES= YES +% +% 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 ) +% United States customary units (US): ( inches, slug, Rankines, lbf = slug ft/s^2, +% psf = lbf/ft^2, Density = slug/ft^3, +% Speed = ft/s, Equiv. Area = ft^2 ) +SYSTEM_MEASUREMENTS= SI +% +% +% ------------------------------- SOLVER CONTROL ------------------------------% +% +% Maximum number of inner iterations +INNER_ITER= 1000000 +% +% Maximum number of outer iterations (only for multizone problems) +OUTER_ITER= 1 +% +% Maximum number of time iterations +TIME_ITER= 1 +% +% Convergence field +CONV_FIELD= RMS_DENSITY +% +% Min value of the residual (log10 of the residual) +CONV_RESIDUAL_MINVAL= -15 +% +% Start convergence criteria at iteration number +CONV_STARTITER= 10 +% +% Number of elements to apply the criteria +CONV_CAUCHY_ELEMS= 100 +% +% Epsilon to control the series convergence +CONV_CAUCHY_EPS= 1E-10 +% +% Iteration number to begin unsteady restarts +RESTART_ITER= 208 +% +%% Time convergence monitoring +WINDOW_CAUCHY_CRIT = NO +% +% List of time convergence fields +CONV_WINDOW_FIELD = (TAVG_DRAG, TAVG_LIFT) +% +% Time Convergence Monitoring starts at Iteration WINDOW_START_ITER + CONV_WINDOW_STARTITER +CONV_WINDOW_STARTITER = 0 +% +% Epsilon to control the series convergence +CONV_WINDOW_CAUCHY_EPS = 1E-3 +% +% Number of elements to apply the criteria +CONV_WINDOW_CAUCHY_ELEMS = 10 +% +% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% +% +% Mach number (non-dimensional, based on the free-stream values) +MACH_NUMBER= 0.16719966920674 +% +% Angle of attack (degrees, only for compressible flows) +AOA= 0.0 +% +% Side-slip angle (degrees, only for compressible flows) +SIDESLIP_ANGLE= 0.0 +% +% Init option to choose between Reynolds (default) or thermodynamics quantities +% for initializing the solution (REYNOLDS, TD_CONDITIONS) +INIT_OPTION= TD_CONDITIONS +% +% Free-stream option to choose between density and temperature (default) for +% initializing the solution (TEMPERATURE_FS, DENSITY_FS) +FREESTREAM_OPTION= DENSITY_FS +% +% Free-stream pressure (101325.0 N/m^2, 2116.216 psf by default) +FREESTREAM_PRESSURE= 101325.0 +% +% Free-stream temperature (288.15 K, 518.67 R by default) +FREESTREAM_TEMPERATURE= 288.15 +% +% Free-stream VIBRATIONAL temperature (288.15 K, 518.67 R by default) +FREESTREAM_TEMPERATURE_VE= 288.15 +% +% Reynolds number (non-dimensional, based on the free-stream values) +REYNOLDS_NUMBER= 3.8951057985067e+6 +% +% Reynolds length (1 m, 1 inch by default) +REYNOLDS_LENGTH= 1.0 +% +% Free-stream density (1.2886 Kg/m^3, 0.0025 slug/ft^3 by default) +FREESTREAM_DENSITY= 1.225 +% +% Free-stream velocity (1.0 m/s, 1.0 ft/s by default) +FREESTREAM_VELOCITY= ( 56.897550640000, 0.0, 0.0 ) +% +% Free-stream viscosity (1.853E-5 N s/m^2, 3.87E-7 lbf s/ft^2 by default) +FREESTREAM_VISCOSITY= 1.78938027807758E-05 +% +% Compressible flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE, +% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE) +REF_DIMENSIONALIZATION= DIMENSIONAL +% +% Free-stream Turbulence Intensity +FREESTREAM_TURBULENCEINTENSITY = 0.001 +% +% Free-stream Turbulent to Laminar viscosity ratio +FREESTREAM_TURB2LAMVISCRATIO = 10 +% +FREESTREAM_NU_FACTOR= 3.0 +% +% ----------------------------- CL DRIVER DEFINITION ---------------------------% +% +% Activate fixed lift mode (specify a CL instead of AoA, NO/YES) +FIXED_CL_MODE= NO +% +% Target coefficient of lift for fixed lift mode (0.80 by default) +TARGET_CL= 0.58 +% +% Estimation of dCL/dAlpha (0.2 per degree by default) +DCL_DALPHA= 0.11 +% +% Maximum number of iterations between AoA updates +UPDATE_AOA_ITER_LIMIT= 2500 +% +% Number of iterations to evaluate dCL_dAlpha by using finite differences (500 by default) +ITER_DCL_DALPHA= 500 + +% ---------------------- REFERENCE VALUE DEFINITION ---------------------------% +% +% Reference origin for moment computation (m or in) +REF_ORIGIN_MOMENT_X = 0.00 +REF_ORIGIN_MOMENT_Y = 0.00 +REF_ORIGIN_MOMENT_Z = 0.00 +% +% 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= 1.0 +% +% Aircraft semi-span (0 implies automatic calculation) (m or in) +SEMI_SPAN= 1.0 + +% ---- NONEQUILIBRIUM GAS, IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------% +% +% Fluid model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS, +% CONSTANT_DENSITY, INC_IDEAL_GAS, INC_IDEAL_GAS_POLY, MUTATIONPP, USER_DEFINED_NONEQ) +FLUID_MODEL= STANDARD_AIR +% +% Ratio of specific heats (1.4 default and the value is hardcoded +% for the model STANDARD_AIR, compressible only) +GAMMA_VALUE= 1.4 +% +% Specific gas constant (287.058 J/kg*K default and this value is hardcoded +% for the model STANDARD_AIR, compressible only) +GAS_CONSTANT= 287.058 +% +% Critical Temperature (131.00 K by default) +CRITICAL_TEMPERATURE= 131.00 +% +% Critical Pressure (3588550.0 N/m^2 by default) +CRITICAL_PRESSURE= 3588550.0 +% +% Acentri factor (0.035 (air)) +ACENTRIC_FACTOR= 0.035 +% +% Specific heat at constant pressure, Cp (1004.703 J/kg*K (air)). +% Incompressible fluids with energy eqn. only (CONSTANT_DENSITY, INC_IDEAL_GAS). +SPECIFIC_HEAT_CP= 1004.703 +% +% Thermal expansion coefficient (0.00347 K^-1 (air)) +% Used with Boussinesq approx. (incompressible, BOUSSINESQ density model only) +THERMAL_EXPANSION_COEFF= 0.00347 +% +% Molecular weight for an incompressible ideal gas (28.96 g/mol (air) default) +MOLECULAR_WEIGHT= 28.96 +% +% Temperature polynomial coefficients (up to quartic) for specific heat Cp. +% Format -> Cp(T) : b0 + b1*T + b2*T^2 + b3*T^3 + b4*T^4 +CP_POLYCOEFFS= (0.0, 0.0, 0.0, 0.0, 0.0) + +% --------------------------- VISCOSITY MODEL ---------------------------------% +% +% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY, POLYNOMIAL_VISCOSITY). +VISCOSITY_MODEL= SUTHERLAND +% +% Molecular Viscosity that would be constant (1.716E-5 by default) +MU_CONSTANT= 1.716E-5 +% +% Sutherland Viscosity Ref (1.716E-5 default value for AIR SI) +MU_REF= 1.716E-5 +% +% Sutherland Temperature Ref (273.15 K default value for AIR SI) +MU_T_REF= 273.15 +% +% Sutherland constant (110.4 default value for AIR SI) +SUTHERLAND_CONSTANT= 110.4 +% +% Temperature polynomial coefficients (up to quartic) for viscosity. +% Format -> Mu(T) : b0 + b1*T + b2*T^2 + b3*T^3 + b4*T^4 +MU_POLYCOEFFS= (0.0, 0.0, 0.0, 0.0, 0.0) + +% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------% +% +% Laminar Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL, +% POLYNOMIAL_CONDUCTIVITY). +CONDUCTIVITY_MODEL= CONSTANT_PRANDTL +% +% Molecular Thermal Conductivity that would be constant (0.0257 by default) +THERMAL_CONDUCTIVITY_CONSTANT= 0.0257 +% +% Laminar Prandtl number (0.72 (air), only for CONSTANT_PRANDTL) +PRANDTL_LAM= 0.72 +% +% Temperature polynomial coefficients (up to quartic) for conductivity. +% Format -> Kt(T) : b0 + b1*T + b2*T^2 + b3*T^3 + b4*T^4 +KT_POLYCOEFFS= (0.0, 0.0, 0.0, 0.0, 0.0) +% +% Definition of the turbulent thermal conductivity model for RANS +% (CONSTANT_PRANDTL_TURB by default, NONE). +TURBULENT_CONDUCTIVITY_MODEL= CONSTANT_PRANDTL_TURB +% +% Turbulent Prandtl number (0.9 (air) by default) +PRANDTL_TURB= 0.90 +% ----------------------- DYNAMIC MESH DEFINITION -----------------------------% +% +% Type of dynamic mesh (NONE, RIGID_MOTION, ROTATING_FRAME, +% STEADY_TRANSLATION, GUST) +% ROTATING_FRAME: This option considers both parameters ROTATION_RATE and +% TRANSLATION_RATE, which allows to simulate a free-flying aircraft (in a flight +% mechanical sense) which moves and rotates in all six degrees of freedom about +% the center of gravity. In this context, the farfield MACH number is set to +% zero and MACH_MOTION is used instead to compute force coefficients. +% STEADY_TRANSLATION: This option considers only the parameter TRANSLATION_RATE. +% +GRID_MOVEMENT= NONE +% +% Motion mach number (non-dimensional). Used for initializing a viscous flow +% with the Reynolds number and for computing force coeffs. with dynamic meshes. +MACH_MOTION= 0.16719966920674 +% +% Coordinates of the motion origin +MOTION_ORIGIN= 0.0 0.0 0.0 +% +% Angular velocity vector (rad/s) about the motion origin +ROTATION_RATE = 0.0 0.0 0.0 +% +% Pitching angular freq. (rad/s) about the motion origin +PITCHING_OMEGA= 0.0 0.0 0.0 +% +% Pitching amplitude (degrees) about the motion origin +PITCHING_AMPL= 0.0 0.0 0.0 +% +% Pitching phase offset (degrees) about the motion origin +PITCHING_PHASE= 0.0 0.0 0.0 +% +% Translational velocity (m/s or ft/s) in the x, y, & z directions +TRANSLATION_RATE = 0.0 0.0 0.0 +% +% Plunging angular freq. (rad/s) in x, y, & z directions +PLUNGING_OMEGA= 0.0 0.0 0.0 +% +% Plunging amplitude (m or ft) in x, y, & z directions +PLUNGING_AMPL= 0.0 0.1 0.0 +% +% -------------------- BOUNDARY CONDITION DEFINITION --------------------------% +% +% Navier-Stokes (no-slip), constant heat flux wall marker(s) (NONE = no marker) +% Format: ( marker name, constant heat flux (J/m^2), ... ) +MARKER_HEATFLUX= ( INTAKE, 0.0, NOZZLE_TE, 0.0, PLUG_TE, 0.0, PLUG, 0.0, NACELLE_TE, 0.0, SPINNER, 0.0, LIP, 0.0, NOZZLE_INNER, 0.0, NOZZLE, 0.0, NACELLE_INNER, 0.0, COWL, 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), ... ) +% Inc. Pressure: ( outlet marker, back pressure (static gauge in Pa), ... ) +% Inc. Mass Flow: ( outlet marker, mass flow target (kg/s), ... ) +%MARKER_OUTLET= ( OUT, 101325.0 ) +% +% Symmetry boundary marker(s) (NONE = no marker) +%MARKER_SYM= ( SYM ) +% +% Engine Inflow boundary type (FAN_FACE_MACH, FAN_FACE_PRESSURE, FAN_FACE_MDOT) +ENGINE_INFLOW_TYPE= FAN_FACE_MDOT +ENGINE_EXHAUST_TO_INLET= YES +% +% Damping factor for the engine inflow. +DAMP_ENGINE_INFLOW= 0.01 +% +% Engine inflow boundary marker(s) (NONE = no marker) +% Format: (engine inflow marker, fan face Mach, ... ) +MARKER_ENGINE_INFLOW= ( FAN_IN, 140.0 ) +% +% Engine exhaust boundary marker(s) with the following formats (NONE = no marker) +% Format: (engine exhaust marker, total nozzle temp, total nozzle pressure, ... ) +MARKER_ENGINE_EXHAUST= ( FAN_OUT, 289.761088684333, 103321.726628227, CORE_OUT, 289.761088684333, 103321.726628227 ) +% +% Engine nu factor (SA model). +ENGINE_NU_FACTOR= 3.0 +% +% ------------------------ SURFACES IDENTIFICATION ----------------------------% +% +% Marker(s) of the surface in the surface flow solution file +MARKER_PLOTTING = ( NOZZLE_TE, PLUG_TE, PLUG, NACELLE_TE, SPINNER, LIP, INTAKE, NOZZLE_INNER, NOZZLE, NACELLE_INNER, COWL, FAN_IN, FAN_OUT, CORE_OUT ) +% +% Marker(s) of the surface where the non-dimensional coefficients are evaluated. +MARKER_MONITORING = ( NACELLE_TE, LIP, COWL ) +% +% Marker(s) of the surface that is going to be analyzed in detail (massflow, average pressure, distortion, etc) +MARKER_ANALYZE = ( FAN_IN, FAN_OUT, CORE_OUT ) +% +% 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 + +% Numerical method for spatial gradients to be used for MUSCL reconstruction +% Options are (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES, LEAST_SQUARES). Default value is +% NONE and the method specified in NUM_METHOD_GRAD is used. +NUM_METHOD_GRAD_RECON = GREEN_GAUSS +% +% CFL number (initial value for the adaptive CFL number) +CFL_NUMBER= 1.0 +% +% Adaptive CFL number (NO, YES) +CFL_ADAPT= NO +% +% Parameters of the adaptive CFL number (factor down, factor up, CFL min value, +% CFL max value ) +CFL_ADAPT_PARAM= ( 0.1, 2.0, 0.1, 1.0 ) +% +% Maximum Delta Time in local time stepping simulations +MAX_DELTA_TIME= 1E6 +% +% Runge-Kutta alpha coefficients +RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) +% +% 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 +% +% List of weighting values when using more than one OBJECTIVE_FUNCTION. Separate by commas and match with MARKER_MONITORING. +OBJECTIVE_WEIGHT = 1.0 + +% ----------- SLOPE LIMITER AND DISSIPATION SENSOR DEFINITION -----------------% +% +% Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations. +% Required for 2nd order upwind schemes (NO, YES) +MUSCL_FLOW= NO +% +% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG, +% BARTH_JESPERSEN, VAN_ALBADA_EDGE) +SLOPE_LIMITER_FLOW= VENKATAKRISHNAN +% +% Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations. +% Required for 2nd order upwind schemes (NO, YES) +MUSCL_TURB= YES +% +% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG, +% BARTH_JESPERSEN, VAN_ALBADA_EDGE) +SLOPE_LIMITER_TURB= VENKATAKRISHNAN +% +% Monotonic Upwind Scheme for Conservation Laws (TVD) in the adjoint flow equations. +% Required for 2nd order upwind schemes (NO, YES) +MUSCL_ADJFLOW= YES +% +% Slope limiter (NONE, VENKATAKRISHNAN, BARTH_JESPERSEN, VAN_ALBADA_EDGE, +% SHARP_EDGES, WALL_DISTANCE) +SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN +% +% Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence adjoint equations. +% Required for 2nd order upwind schemes (NO, YES) +MUSCL_ADJTURB= NO +% +% Slope limiter (NONE, VENKATAKRISHNAN, BARTH_JESPERSEN, VAN_ALBADA_EDGE) +SLOPE_LIMITER_ADJTURB= VENKATAKRISHNAN +% +% Coefficient for the Venkat's limiter (upwind scheme). A larger values decrease +% the extent of limiting, values approaching zero cause +% lower-order approximation to the solution (0.05 by default) +VENKAT_LIMITER_COEFF= 0.05 +% +% Reference coefficient for detecting sharp edges (3.0 by default). +REF_SHARP_EDGES = 3.0 +% +% Coefficient for the adjoint sharp edges limiter (3.0 by default). +ADJ_SHARP_LIMITER_COEFF= 3.0 +% +% Remove sharp edges from the sensitivity evaluation (NO, YES) +SENS_REMOVE_SHARP = NO +% +% Freeze the value of the limiter after a number of iterations +LIMITER_ITER= 999999 +% +% 1st order artificial dissipation coefficients for +% the Lax–Friedrichs method ( 0.15 by default ) +LAX_SENSOR_COEFF= 0.15 +% +% 2nd and 4th order artificial dissipation coefficients for +% the JST method ( 0.5, 0.02 by default ) +JST_SENSOR_COEFF= ( 0.5, 0.02 ) +% +% 1st order artificial dissipation coefficients for +% the adjoint Lax–Friedrichs method ( 0.15 by default ) +ADJ_LAX_SENSOR_COEFF= 0.15 +% +% 2nd, and 4th order artificial dissipation coefficients for +% the adjoint JST method ( 0.5, 0.02 by default ) +ADJ_JST_SENSOR_COEFF= ( 0.5, 0.02 ) + +% ------------------------ LINEAR SOLVER DEFINITION ---------------------------% +% +% Linear solver or smoother for implicit formulations: +% BCGSTAB, FGMRES, RESTARTED_FGMRES, CONJUGATE_GRADIENT (self-adjoint problems only), SMOOTHER. +LINEAR_SOLVER= FGMRES +% +% Same for discrete adjoint (smoothers not supported) +DISCADJ_LIN_SOLVER= FGMRES +% +% Preconditioner of the Krylov linear solver or type of smoother (ILU, LU_SGS, LINELET, JACOBI) +LINEAR_SOLVER_PREC= ILU +% +% Same for discrete adjoint (JACOBI or ILU) +DISCADJ_LIN_PREC= ILU +% +% Linael solver ILU preconditioner fill-in level (0 by default) +LINEAR_SOLVER_ILU_FILL_IN= 0 +% +% Minimum error of the linear solver for implicit formulations +LINEAR_SOLVER_ERROR= 1E-6 +% +% Max number of iterations of the linear solver for the implicit formulation +LINEAR_SOLVER_ITER= 5 +% +% Restart frequency for RESTARTED_FGMRES +LINEAR_SOLVER_RESTART_FREQUENCY= 10 +% +% Relaxation factor for smoother-type solvers (LINEAR_SOLVER= SMOOTHER) +LINEAR_SOLVER_SMOOTHER_RELAXATION= 1.0 + +% -------------------------- MULTIGRID PARAMETERS -----------------------------% +% +% Multi-grid levels (0 = no multi-grid) +MGLEVEL= 0 +% +% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE) +MGCYCLE= V_CYCLE +% +% Multi-grid pre-smoothing level +MG_PRE_SMOOTH= ( 1, 2, 3, 3 ) +% +% Multi-grid post-smoothing level +MG_POST_SMOOTH= ( 0, 0, 0, 0 ) +% +% Jacobi implicit smoothing of the correction +MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 ) +% +% Damping factor for the residual restriction +MG_DAMP_RESTRICTION= 0.75 +% +% Damping factor for the correction prolongation +MG_DAMP_PROLONGATION= 0.75 + +% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% +% +% Convective numerical method (JST, JST_KE, JST_MAT, LAX-FRIEDRICH, CUSP, ROE, AUSM, +% AUSMPLUSUP, AUSMPLUSUP2, AUSMPWPLUS, HLLC, TURKEL_PREC, +% SW, MSW, FDS, SLAU, SLAU2, L2ROE, LMROE) +CONV_NUM_METHOD_FLOW= JST +% +% Roe Low Dissipation function for Hybrid RANS/LES simulations (FD, NTS, NTS_DUCROS) +ROE_LOW_DISSIPATION= NONE +% +% Post-reconstruction correction for low Mach number flows (NO, YES) +LOW_MACH_CORR= NO +% +% Roe-Turkel preconditioning for low Mach number flows (NO, YES) +LOW_MACH_PREC= YES +% +% Use numerically computed Jacobians for AUSM+up(2) and SLAU(2) +% Slower per iteration but potentialy more stable and capable of higher CFL +USE_ACCURATE_FLUX_JACOBIANS= NO +% +% Use the vectorized version of the selected numerical method (available for JST family and Roe). +% SU2 should be compiled for an AVX or AVX512 architecture for best performance. +USE_VECTORIZATION= NO +% +% Entropy fix coefficient (0.0 implies no entropy fixing, 1.0 implies scalar +% artificial dissipation) +ENTROPY_FIX_COEFF= 0.001 +% +% Higher values than 1 (3 to 4) make the global Jacobian of central schemes (compressible flow +% only) more diagonal dominant (but mathematically incorrect) so that higher CFL can be used. +CENTRAL_JACOBIAN_FIX_FACTOR= 4.0 +% +% 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 +% +% Time discretization (EULER_IMPLICIT) +TIME_DISCRE_TURB= EULER_IMPLICIT +% +% Reduction factor of the CFL coefficient in the turbulence problem +CFL_REDUCTION_TURB= 1.0 + +% --------------------- HEAT NUMERICAL METHOD DEFINITION ----------------------% +% +% Value of the thermal diffusivity +%THERMAL_DIFFUSIVITY= 1.0 + +% ------------------------- SCREEN/HISTORY VOLUME OUTPUT --------------------------% +% +% Screen output fields (use 'SU2_CFD -d ' to view list of available fields) +SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, LIFT, DRAG) +% +% History output groups (use 'SU2_CFD -d ' to view list of available fields) +HISTORY_OUTPUT= (ITER, AERO_COEFF, RMS_RES, AOA, NONPHYSICAL_POINTS, SURFACE_MASSFLOW, SURFACE_STATIC_PRESSURE) +% +% Volume output fields/groups (use 'SU2_CFD -d ' to view list of available fields) +VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE) +% +% Writing frequency for screen output +SCREEN_WRT_FREQ_INNER= 1 +% +SCREEN_WRT_FREQ_OUTER= 1 +% +SCREEN_WRT_FREQ_TIME= 1 +% +% Writing frequency for history output +HISTORY_WRT_FREQ_INNER= 1 +% +HISTORY_WRT_FREQ_OUTER= 1 +% +HISTORY_WRT_FREQ_TIME= 1 +% +% list of writing frequencies corresponding to the list in OUTPUT_FILES +OUTPUT_WRT_FREQ= 1000 +% +% Output the performance summary to the console at the end of SU2_CFD +WRT_PERFORMANCE= NO +% +% Overwrite or append iteration number to the restart files when saving +WRT_RESTART_OVERWRITE= YES +% +% Overwrite or append iteration number to the surface files when saving +WRT_SURFACE_OVERWRITE= YES +% +% Overwrite or append iteration number to the volume files when saving +WRT_VOLUME_OVERWRITE= YES +% +WRT_FORCES_BREAKDOWN= YES +% +% ------------------------- INPUT/OUTPUT FILE INFORMATION --------------------------% +% +% Mesh input file +MESH_FILENAME= engine-alone.cgns +% +% Mesh input file format (SU2, CGNS) +MESH_FORMAT= CGNS +% +% Mesh output file +MESH_OUT_FILENAME= mesh_out.su2 +% +% Restart flow input file +SOLUTION_FILENAME= solution_flow.dat +% +% Restart adjoint input file +SOLUTION_ADJ_FILENAME= solution_adj.dat +% +% Output tabular file format (TECPLOT, CSV) +TABULAR_FORMAT= TECPLOT +% +% Files to output +% Possible formats : (TECPLOT_ASCII, TECPLOT, SURFACE_TECPLOT_ASCII, +% SURFACE_TECPLOT, CSV, SURFACE_CSV, PARAVIEW_ASCII, PARAVIEW_LEGACY, SURFACE_PARAVIEW_ASCII, +% SURFACE_PARAVIEW_LEGACY, PARAVIEW, SURFACE_PARAVIEW, RESTART_ASCII, RESTART, CGNS, SURFACE_CGNS, STL_ASCII, STL_BINARY) +% default : (RESTART, PARAVIEW, SURFACE_PARAVIEW) +OUTPUT_FILES= (RESTART, TECPLOT, SURFACE_TECPLOT) +% +% Output file convergence history (w/o extension) +CONV_FILENAME= history +% +% Output file with the forces breakdown +BREAKDOWN_FILENAME= forces_breakdown.dat +% +% Output file restart flow +RESTART_FILENAME= restart_flow.dat +% +% Output file restart adjoint +RESTART_ADJ_FILENAME= restart_adj.dat +% +% Output file flow (w/o extension) variables +VOLUME_FILENAME= flow +% +% Output file adjoint (w/o extension) variables +VOLUME_ADJ_FILENAME= adjoint +% +% Output Objective function +VALUE_OBJFUNC_FILENAME= of_eval.dat +% +% Output objective function gradient (using continuous adjoint) +GRAD_OBJFUNC_FILENAME= of_grad.dat +% +% Output file surface flow coefficient (w/o extension) +SURFACE_FILENAME= surface_flow +% +% Output file surface adjoint coefficient (w/o extension) +SURFACE_ADJ_FILENAME= surface_adjoint +% +% Read binary restart files (YES, NO) +READ_BINARY_RESTART= YES +% +% Reorient elements based on potential negative volumes (YES/NO) +REORIENT_ELEMENTS= YES diff --git a/config_template.cfg b/config_template.cfg index aa22fc17771..0dd67764bdf 100644 --- a/config_template.cfg +++ b/config_template.cfg @@ -1183,6 +1183,9 @@ MARKER_ENGINE_INFLOW= ( NONE ) % Format: (engine exhaust marker, total nozzle temp, total nozzle pressure, ... ) MARKER_ENGINE_EXHAUST= ( NONE ) % +% Flag to allow mass-flow rate coupling between all exhaust surfaces and the engine inlet (YES, NO) +ENGINE_EXHAUST_TO_INLET= NO +% % Displacement boundary marker(s) (NONE = no marker) % Format: ( displacement marker, displacement value normal to the surface, ... ) MARKER_NORMAL_DISPL= ( NONE )