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July 15, 2021, 03:04 |
Optimization of Nozzle in SU2
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New Member
Abhishek Karn
Join Date: Jul 2021
Posts: 2
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am trying to optimize nozzle shape for maximum mach number. I am confused whether I can SURFACE_MACH objective function for that purpose. When I optimize for SURFACE_MACH , I get 0 gradient .
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% % % Physical governing equations (EULER, NAVIER_STOKES, % FEM_EULER, FEM_NAVIER_STOKES, FEM_RANS, FEM_LES, % WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY, % POISSON_EQUATION) SOLVER= RANS % % Specify turbulence model (NONE, SA, SA_NEG, SST, SA_E, SA_COMP, SA_E_COMP) KIND_TURB_MODEL= SST % % Mathematical problem (DIRECT, CONTINUOUS_ADJOINT, DISCRETE_ADJOINT) MATH_PROBLEM= CONTINUOUS_ADJOINT % % Restart solution (NO, YES) RESTART_SOL= 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 % % -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% % % Mach number (non-dimensional, based on the free-stream values) MACH_NUMBER= 0.086 % % 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= TEMPERATURE_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 % % Compressible flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE, % FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE) REF_DIMENSIONALIZATION= DIMENSIONAL % ---- 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) 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 % % Acentric factor (0.035 (air)) ACENTRIC_FACTOR= 0.035 % --------------------------- VISCOSITY MODEL ---------------------------------% % % Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY, POLYNOMIAL_VISCOSITY). VISCOSITY_MODEL= CONSTANT_VISCOSITY % % Molecular Viscosity that would be constant (1.716E-5 by default) MU_CONSTANT= 1.716E-05 % --------------------------- 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) KT_CONSTANT= 0.0257 % -------------------- 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= ( WALL, 0.0 ) % % Symmetry boundary marker(s) (NONE = no marker) MARKER_SYM= ( SYMMETRY) % % Riemann boundary marker(s) (NONE = no marker) % Format: (marker, data kind flag, list of data) MARKER_RIEMANN= ( INFLOW, TOTAL_CONDITIONS_PT, 101831.3, 286.75, 1.0, 0.0, 0.0, OUTFLOW, STATIC_PRESSURE, 500, 0.0, 0.0, 0.0, 0.0 ) % -------------------- 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= 0.5 % ------------------------ SURFACES IDENTIFICATION ----------------------------% % % Marker of the surface which is going to be plotted or designed MARKER_PLOTTING= ( INFLOW,WALL ,OUTFLOW,SYMMETRY) % % Marker of the surface where the functional (Cd, Cl, etc.) will be evaluated MARKER_MONITORING= ( INFLOW,WALL ,OUTFLOW,SYMMETRY) % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% % % Numerical method for spatial gradients (GREEN_GAUSS, LEAST_SQUARES, % WEIGHTED_LEAST_SQUARES) NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES % % Courant-Friedrichs-Lewy condition of the finest grid CFL_NUMBER= 0.5 % % 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= ( 0.5, 1, 1.0, 100.0 ) % % Runge-Kutta alpha coefficients RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) % % Linear solver for the implicit formulation (BCGSTAB, FGMRES) LINEAR_SOLVER= BCGSTAB % % Min error of the linear solver for the implicit formulation LINEAR_SOLVER_ERROR= 1E-6 % % Max number of iterations of the linear solver for the implicit formulation LINEAR_SOLVER_ITER= 5 % % Preconditioner of the Krylov linear solver (ILU, LU_SGS, LINELET, JACOBI) LINEAR_SOLVER_PREC= ILU % % Linael solver ILU preconditioner fill-in level (1 by default) LINEAR_SOLVER_ILU_FILL_IN= 0 % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% % % Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC, % TURKEL_PREC, MSW) CONV_NUM_METHOD_FLOW= ROE % % Coefficient for the limiter (smooth regions) VENKAT_LIMITER_COEFF= 0.006 % % 2nd and 4th order artificial dissipation coefficients JST_SENSOR_COEFF= ( 0.5, 0.02 ) % % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) TIME_DISCRE_FLOW= EULER_IMPLICIT % ----------- 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= YES % % Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG, % BARTH_JESPERSEN, VAN_ALBADA_EDGE) SLOPE_LIMITER_FLOW= NONE % % Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations. % Required for 2nd order upwind schemes (NO, YES) MUSCL_TURB= NO % -------------------------- MULTIGRID PARAMETERS -----------------------------% % % Multi-Grid Levels (0 = no multi-grid) MGLEVEL= 2 % % 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= 0.8 % % Damping factor for the correction prolongation MG_DAMP_PROLONGATION= 0.8 % ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------% % % Convective numerical method (JST, LAX-FRIEDRICH, ROE) CONV_NUM_METHOD_ADJFLOW= ROE % % 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= NONE % % 2nd, and 4th order artificial dissipation coefficients ADJ_JST_SENSOR_COEFF= ( 0.5, 0.02 ) % % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT) TIME_DISCRE_ADJFLOW= EULER_IMPLICIT % % Relaxation coefficient RELAXATION_FACTOR_ADJOINT= 1.0 % % Reduction factor of the CFL coefficient in the adjoint problem CFL_REDUCTION_ADJFLOW= 0.8 % % Limit value for the adjoint variable LIMIT_ADJFLOW= 1E15 % % Multigrid adjoint problem (NO, YES) MG_ADJFLOW= NO % % Objective function in gradient evaluation (DRAG, LIFT, SIDEFORCE, MOMENT_X, % MOMENT_Y, MOMENT_Z, EFFICIENCY, % EQUIVALENT_AREA, NEARFIELD_PRESSURE, % FORCE_X, FORCE_Y, FORCE_Z, THRUST, % TORQUE, FREE_SURFACE, TOTAL_HEATFLUX, % MAXIMUM_HEATFLUX, INVERSE_DESIGN_PRESSURE, % INVERSE_DESIGN_HEATFLUX, SURFACE_TOTAL_PRESSURE, % SURFACE_MASSFLOW) % For a weighted sum of objectives: separate by commas, add OBJECTIVE_WEIGHT and MARKER_MONITORING in matching order. OBJECTIVE_FUNCTION = SURFACE_MACH % % List of weighting values when using more than one OBJECTIVE_FUNCTION. Separate by commas and match with MARKER_MONITORING. OBJECTIVE_WEIGHT= -1.0E-7,1.0 % Marker on which to track one-dimensionalized quantities MARKER_ANALYZE = (WALL) % % Method to compute the average value in MARKER_ANALYZE (AREA, MASSFLUX). MARKER_ANALYZE_AVERAGE = AREA % --------------------------- CONVERGENCE PARAMETERS --------------------------% % % Number of total iterations ITER= 100 % % Convergence criteria (CAUCHY, RESIDUAL) % CONV_CRITERIA= RESIDUAL % % % Min value of the residual (log10 of the residual) CONV_RESIDUAL_MINVAL= -24 % % Start convergence criteria at iteration number CONV_STARTITER= 10 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % % Mesh input file MESH_FILENAME= half_nozzle6.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= solution_flow.dat % % Restart adjoint input file SOLUTION_ADJ_FILENAME= solution_adj.dat % % Output file format (TECPLOT, TECPLOT_BINARY, PARAVIEW, PARAVIEW_BINARY, % FIELDVIEW, FIELDVIEW_BINARY) TABULAR_FORMAT= CSV % % Output file convergence history (w/o extension) CONV_FILENAME= history % % Output file restart flow RESTART_FILENAME= restart_flow.dat % % Output file flow (w/o extension) variables VOLUME_FILENAME= flow % % Output file restart adjoint RESTART_ADJ_FILENAME= restart_adj.dat % % Output file adjoint (w/o extension) variables VOLUME_ADJ_FILENAME= adjoint % % 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 % % Writing solution file frequency OUTPUT_WRT_FREQ= 1000 % % Screen output SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_TKE, RMS_DISSIPATION, CL,CD) % Output files OUTPUT_FILES = (RESTART, PARAVIEW, SURFACE_PARAVIEW, SURFACE_CSV) % -------------------- FREE-FORM DEFORMATION PARAMETERS -----------------------% % % Tolerance of the Free-Form Deformation point inversion FFD_TOLERANCE= 1E-10 % % Maximum number of iterations in the Free-Form Deformation point inversion FFD_ITERATIONS= 500 % % FFD box definition: 3D case (FFD_BoxTag, X1, Y1, Z1, X2, Y2, Z2, X3, Y3, Z3, X4, Y4, Z4, % X5, Y5, Z5, X6, Y6, Z6, X7, Y7, Z7, X8, Y8, Z8) % 2D case (FFD_BoxTag, X1, Y1, 0.0, X2, Y2, 0.0, X3, Y3, 0.0, X4, Y4, 0.0, % 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0) FFD_DEFINITION= (MAIN_BOX, -0.04, 0.01, 0, 0.04, 0.01, 0, 0.04, 0.05, 0, -0.04, 0.05, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0) % % FFD box degree: 3D case (x_degree, y_degree, z_degree) % 2D case (x_degree, y_degree, 0) FFD_DEGREE= (12, 1,0) % % Surface continuity at the intersection with the FFD (1ST_DERIVATIVE, 2ND_DERIVATIVE) FFD_CONTINUITY= 2ND_DERIVATIVE % ------------------------ GRID DEFORMATION PARAMETERS ------------------------% % % Kind of deformation (FFD_SETTING, HICKS_HENNE, HICKS_HENNE_NORMAL, PARABOLIC, % HICKS_HENNE_SHOCK, NACA_4DIGITS, DISPLACEMENT, ROTATION, % FFD_CONTROL_POINT, FFD_DIHEDRAL_ANGLE, FFD_TWIST_ANGLE, % FFD_ROTATION) % Marker of the surface in which we are going apply the shape deformation DV_MARKER= ( WALL) % DV_KIND= FFD_CONTROL_POINT_2D % % % Parameters of the shape deformation % - HICKS_HENNE_FAMILY ( Lower(0)/Upper(1) side, x_Loc ) % - NACA_4DIGITS ( 1st digit, 2nd digit, 3rd and 4th digit ) % - PARABOLIC ( 1st digit, 2nd and 3rd digit ) % - DISPLACEMENT ( x_Disp, y_Disp, z_Disp ) % - FFD_CONTROL_POINT ( FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Disp, y_Disp, z_Disp ) % - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) DV_PARAM= (MAIN_BOX, 6,0, 0,0,1.0,0 ) % % Value of the shape deformation deformation DV_VALUE= 0.0 % Number of smoothing iterations for FEA mesh deformation DEFORM_LINEAR_SOLVER_ITER= 500 % % Number of nonlinear deformation iterations (surface deformation increments) DEFORM_NONLINEAR_ITER= 1 % % Print the residuals during mesh deformation to the console (YES, NO) DEFORM_CONSOLE_OUTPUT= YES % % Minimum residual criteria for the linear solver convergence of grid deformation DEFORM_LINEAR_SOLVER_ERROR= 1E-14 % % Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME, % WALL_DISTANCE, CONSTANT_STIFFNESS) DEFORM_STIFFNESS_TYPE= WALL_DISTANCE % --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------% % % Available flow based objective functions or constraint functions % DRAG, LIFT, SIDEFORCE, EFFICIENCY, BUFFET, % FORCE_X, FORCE_Y, FORCE_Z, % MOMENT_X, MOMENT_Y, MOMENT_Z, % THRUST, TORQUE, FIGURE_OF_MERIT, % EQUIVALENT_AREA, NEARFIELD_PRESSURE, % TOTAL_HEATFLUX, MAXIMUM_HEATFLUX, % INVERSE_DESIGN_PRESSURE, INVERSE_DESIGN_HEATFLUX, % SURFACE_TOTAL_PRESSURE, SURFACE_MASSFLOW % SURFACE_STATIC_PRESSURE, SURFACE_MACH % % Available geometrical based objective functions or constraint functions % AIRFOIL_AREA, AIRFOIL_THICKNESS, AIRFOIL_CHORD, AIRFOIL_TOC, AIRFOIL_AOA, % WING_VOLUME, WING_MIN_THICKNESS, WING_MAX_THICKNESS, WING_MAX_CHORD, WING_MIN_TOC, WING_MAX_TWIST, WING_MAX_CURVATURE, WING_MAX_DIHEDRAL % STATION#_WIDTH, STATION#_AREA, STATION#_THICKNESS, STATION#_CHORD, STATION#_TOC, % STATION#_TWIST (where # is the index of the station defined in GEO_LOCATION_STATIONS) % % Available design variables % 2D Design variables % FFD_CONTROL_POINT_2D ( 19, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind, x_Mov, y_Mov ) % FFD_CAMBER_2D ( 20, Scale | Mark. List | FFD_BoxTag, i_Ind ) % FFD_THICKNESS_2D ( 21, Scale | Mark. List | FFD_BoxTag, i_Ind ) % FFD_TWIST_2D ( 22, Scale | Mark. List | FFD_BoxTag, x_Orig, y_Orig ) % HICKS_HENNE ( 30, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc ) % ANGLE_OF_ATTACK ( 101, Scale | Mark. List | 1.0 ) % % 3D Design variables % FFD_CONTROL_POINT ( 11, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Mov, y_Mov, z_Mov ) % FFD_NACELLE ( 12, Scale | Mark. List | FFD_BoxTag, rho_Ind, theta_Ind, phi_Ind, rho_Mov, phi_Mov ) % FFD_GULL ( 13, Scale | Mark. List | FFD_BoxTag, j_Ind ) % FFD_CAMBER ( 14, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind ) % FFD_TWIST ( 15, Scale | Mark. List | FFD_BoxTag, j_Ind, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) % FFD_THICKNESS ( 16, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind ) % FFD_ROTATION ( 18, Scale | Mark. List | FFD_BoxTag, x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn ) % FFD_ANGLE_OF_ATTACK ( 24, Scale | Mark. List | FFD_BoxTag, 1.0 ) % % Global design variables % TRANSLATION ( 1, Scale | Mark. List | x_Disp, y_Disp, z_Disp ) % ROTATION ( 2, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn ) % % Optimization objective function with scaling factor, separated by semicolons. % To include quadratic penalty function: use OPT_CONSTRAINT option syntax within the OPT_OBJECTIVE list. % ex= Objective * Scale OPT_OBJECTIVE= SURFACE_MACH % % Optimization constraint functions with pushing factors (affects its value, not the gradient % in the python scripts), separated by semicolons % ex= (Objective = Value ) * Scale, use '>','<','=' OPT_CONSTRAINT= NONE % % Factor to reduce the norm of the gradient (affects the objective function and gradient in the python scripts) % In general, a norm of the gradient ~1E-6 is desired. OPT_GRADIENT_FACTOR= 1E-6 % % Factor to relax or accelerate the optimizer convergence (affects the line search in SU2_DEF) % In general, surface deformations of 0.01'' or 0.0001m are desirable OPT_RELAX_FACTOR= 1E3 % % Maximum number of optimizer iterations OPT_ITERATIONS= 100 % % Requested accuracy OPT_ACCURACY= 1E-10 % % Upper bound for each design variable OPT_BOUND_UPPER= 0.020 % % Lower bound for each design variable OPT_BOUND_LOWER= -0.020 % % Optimization design variables, separated by semicolons DEFINITION_DV= ( 19, 1.0| WALL| MAIN_BOX, 1,1,0,1.0);( 19, 1.0| WALL | MAIN_BOX, 2,1,0,1.0);( 19, 1.0| WALL| MAIN_BOX, 3,1,0,1.0);( 19, 1.0| WALL | MAIN_BOX, 4,1,0,1.0);( 19, 1.0| WALL | MAIN_BOX, 5,1,0,1.0);( 19, 1.0| WALL | MAIN_BOX, 6,1,0,1.0);( 19, 1.0| WALL| MAIN_BOX, 7,1,0,1.0);( 19, 1.0| WALL | MAIN_BOX, 8,1,0,1.0);( 19, 1.0| WALL | MAIN_BOX, 9,1,0,1.0);( 19, 1.0| WALL | MAIN_BOX, 10,1,0,1.0) |
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