Replies: 1 comment 4 replies
-
|
Discrete adjoints for turbomachinery are currently broken in the latest version. They are an active area of investigation and I am currently working on them. The time frame for this is hopefully in the next couple of months. |
Beta Was this translation helpful? Give feedback.
-
|
Thanks Josh for your quick reply. Can you guide me which version works correctly for turbomachinery then? |
Beta Was this translation helpful? Give feedback.
-
|
a very old version on a branch called feature_turbomachinery |
Beta Was this translation helpful? Give feedback.
-
|
Hi Josh |
Beta Was this translation helpful? Give feedback.
-
|
Hi 7akashs, I am also researching how to use SU2 for turbomachinery adjoint optimization. Could we exchange contact information? |
Beta Was this translation helpful? Give feedback.
Uh oh!
There was an error while loading. Please reload this page.
-
**No output file is generated when running the SU2 discrete adjoint case for multi-stage compressor **
The configuration file and mesh corresponds to good results when run with SU2_CFD . And Since I am working on an optimization problem, I need to run the case with SU2_CFD_AD to calculate the sensitivities. The solver starts and run successfully, however at the end the simulation stops stating "Storing computational graph wrt MESH COORDINATES." But there must be solution_adj.dat file but no file is written
Here is my configuration file:
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations
SOLVER= RANS
%
% Specify turbulent model (NONE, SA, SST)
KIND_TURB_MODEL= SST
%
MATH_PROBLEM= DISCRETE_ADJOINT
%
% Restart solution (NO, YES)
RESTART_SOL= NO %YES %NO
%
MULTIZONE= YES
%
% List of config files for zone-specific options
CONFIG_LIST= (rotor1.cfg, stator1.cfg, rotor2.cfg, stator2.cfg, rotor3.cfg, stator3.cfg)
%
% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.5 %1.06109
%
% Angle of attack (degrees, only for compressible flows)
AOA= 0.0
%
% Free-stream pressure (101325.0 N/m^2 by default, only Euler flows)
FREESTREAM_PRESSURE= 101325.0
%
% Free-stream temperature (273.15 K by default)
FREESTREAM_TEMPERATURE= 273.15
%
% Free-stream temperature (1.2886 Kg/m3 by default)
FREESTREAM_DENSITY= 1.2886
%
% Free-stream option to choose if you want to use Density (DENSITY_FS) or Temperature TEMPERATURE_FS) to initialize the solution
FREESTREAM_OPTION= TEMPERATURE_FS
%
% Free-stream Turbulence Intensity
FREESTREAM_TURBULENCEINTENSITY = 0.05 %0.025
%
% Free-stream Turbulent to Laminar viscosity ratio
FREESTREAM_TURB2LAMVISCRATIO = 100.0
%
%
%Init option to choose between Reynolds (default) or thermodynamics quantities for initializing the solution (REYNOLDS, TD_CONDITIONS)
INIT_OPTION= TD_CONDITIONS
%
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation
REF_ORIGIN_MOMENT_X = 0.00
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference area for force coefficients (0 implies automatic calculation)
REF_AREA= 1.0
REF_LENGTH= 1.0
%
% Flow non-dimensionalization
REF_DIMENSIONALIZATION= DIMENSIONAL
%
%
% ------------------------------ EQUATION OF STATE ----------------------------%
%
% Different gas model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS)
FLUID_MODEL= IDEAL_GAS
%
% Ratio of specific heats (1.4 default and the value is hardcoded for the model STANDARD_AIR)
GAMMA_VALUE= 1.4
%
% Specific gas constant (287.058 J/kg*K default and this value is hardcoded for the model STANDARD_AIR)
GAS_CONSTANT= 287.058
%
% --------------------------- VISCOSITY MODEL ---------------------------------%
%
% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY).
VISCOSITY_MODEL= SUTHERLAND
%
%
% 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
%
% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
%
% Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL).
CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
%
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
%Navier-Stokes wall boundary marker(s) (NONE = no marker)
MARKER_HEATFLUX= (R1Blade, 0.0, R1Hub, 0.0, R1Shroud, 0.0, S1Blade, 0.0, S1Hub, 0.0, S1Shroud, 0.0, R2Blade, 0.0, R2Hub, 0.0, R2Shroud, 0.0, S2Blade, 0.0, S2Hub, 0.0, S2Shroud, 0.0, R3Blade, 0.0, R3Hub, 0.0, R3Shroud, 0.0, S3Blade, 0.0, S3Hub, 0.0, S3Shroud, 0.0)
%
% Periodic boundary marker(s) (NONE = no marker)
% Format: ( periodic marker, donor marker, rot_cen_x, rot_cen_y, rot_cen_z, rot_angle_x-axis, rot_angle_y-axis, rot_angle_z-axis, translation_x, translation_y, translation_z)
MARKER_PERIODIC= (R1toR1Periodic1Side1, R1toR1Periodic1Side2, 0.0, 0.0, 0.0, 0.0, 0.0, 12.4137931, 0.0, 0.0, 0.0, S1toS1Periodic1Side1, S1toS1Periodic1Side2, 0.0, 0.0, 0.0, 0.0, 0.0, 10.28571428, 0.0, 0.0, 0.0, R2toR2Periodic1Side1, R2toR2Periodic1Side2, 0.0, 0.0, 0.0, 0.0, 0.0, 8.7804878, 0.0, 0.0, 0.0, S2toS2Periodic1Side1, S2toS2Periodic1Side2, 0.0, 0.0, 0.0, 0.0, 0.0, 8.0, 0.0, 0.0, 0.0, R3toR3Periodic1Side1, R3toR3Periodic1Side2, 0.0, 0.0, 0.0, 0.0, 0.0, 7.34693878, 0.0, 0.0, 0.0, S3toS3Periodic1Side1, S3toS3Periodic1Side2, 0.0, 0.0, 0.0, 0.0, 0.0, 6.92307692, 0.0, 0.0, 0.0)
%
%
%-------- INFLOW/OUTFLOW BOUNDARY CONDITION SPECIFIC FOR TURBOMACHINERY --------%
%
% Inflow and Outflow markers must be specified, for each blade (zone), following the natural groth of the machine (i.e, from the first blade to the last)
MARKER_TURBOMACHINERY= (R1Inlet, S1toR1Side2, S1toR1Side1, R2toS1Side2, R2toS1Side1, S2toR2Side2, S2toR2Side1, R3toS2Side2, R3toS2Side1, S3toR3Side2, S3toR3Side1, S3Outlet)
MARKER_ANALYZE = (S3Outlet)
% Mixing-plane interface markers must be specified to activate the transfer of information between zones
MARKER_MIXINGPLANE_INTERFACE= (S1toR1Side2, S1toR1Side1, R2toS1Side2, R2toS1Side1, S2toR2Side2, S2toR2Side1, R3toS2Side2, R3toS2Side1, S3toR3Side2, S3toR3Side1)
% Mixing-plane interface markers must be specified to activate the transfer of information between zones
MARKER_ZONE_INTERFACE= (S1toR1Side2, S1toR1Side1, R2toS1Side2, R2toS1Side1, S2toR2Side2, S2toR2Side1, R3toS2Side2, R3toS2Side1, S3toR3Side2, S3toR3Side1)
%
% Non reflecting boundary condition for inflow, outfolw and mixing-plane
% Format inlet: ( marker, TOTAL_CONDITIONS_PT, Total Pressure , Total Temperature, Flow dir-norm, Flow dir-tang, Flow dir-span, under-relax-avg, under-relax-fourier)
% Format outlet: ( marker, STATIC_PRESSURE, Static Pressure value, -, -, -, -, under-relax-avg, under-relax-fourier)
% Format mixing-plane in and out: ( marker, MIXING_IN or MIXING_OUT, -, -, -, -, -, -, under-relax-avg, under-relax-fourier)
MARKER_GILES= (R1Inlet, TOTAL_CONDITIONS_PT, 101325, 288.15, 1.0, 0.0, 0.0, 0.3, 0.0, S1toR1Side2, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, S1toR1Side1, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, R2toS1Side2, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, R2toS1Side1, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, S2toR2Side2, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, S2toR2Side1, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, R3toS2Side2, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, R3toS2Side1, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, S3toR3Side2, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, S3toR3Side1, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0, 0.3, 0.0, S3Outlet, STATIC_PRESSURE_1D, 180000, 0.0, 0.0, 0.0, 0.0 , 1.0, 0.0)
SPATIAL_FOURIER= NO
%
% This option insert an extra under relaxation factor for the Giles BC at the hub and shroud levels
GILES_EXTRA_RELAXFACTOR= (0.05, 0.05)
%
%---------------------------- TURBOMACHINERY SIMULATION -----------------------------%
%
% Format: (marker)
% If the ROTATING_FRAME option is activated, this option force
% the velocity on the boundaries specified to 0.0
MARKER_SHROUD= (R1Shroud, S1Shroud, R2Shroud, S2Shroud, R3Shroud, S3Shroud)
%
% Specify kind of architecture (AXIAL, CENTRIPETAL, CENTRIFUGAL, CENTRIPETAL_AXIAL)
TURBOMACHINERY_KIND= AXIAL AXIAL AXIAL AXIAL AXIAL AXIAL
%
% Uncomment to work with new_turbo_outputs
TURBO_PERF_KIND= COMPRESSOR COMPRESSOR COMPRESSOR COMPRESSOR COMPRESSOR COMPRESSOR
%
% Specify kind of interpolation for the mixing-plane (LINEAR_INTERPOLATION, NEAREST_SPAN, MATCHING)
MIXINGPLANE_INTERFACE_KIND= LINEAR_INTERPOLATION
%
% Specify option for turbulent mixing-plane (YES, NO) default NO
TURBULENT_MIXINGPLANE= YES
%
% Specify Kind of average process for linearizing the Navier-Stokes equation at inflow and outflow BC included mixing-plane
% (ALGEBRAIC, AREA, MASSSFLUX, MIXEDOUT) default AREA
AVERAGE_PROCESS_KIND= MIXEDOUT
%
% Specify Kind of average process for computing turbomachienry performance parameters
% (ALGEBRAIC, AREA, MASSSFLUX, MIXEDOUT) default AREA
PERFORMANCE_AVERAGE_PROCESS_KIND= MIXEDOUT
%
%Parameters of the Newton method for the MIXEDOUT average algorithm (under relaxation factor, tollerance, max number of iterations)
MIXEDOUT_COEFF= (1.0, 1.0E-05, 15)
%
% Limit of Mach number below which the mixedout algorithm is substituted with a AREA average algorithm
AVERAGE_MACH_LIMIT= 0.03
%
%
% ------------------------ SURFACES IDENTIFICATION ----------------------------%
%
% Marker(s) of the surface in the surface flow solution file
MARKER_PLOTTING= (S3Blade) %(R1Blade, S1Blade, R2Blade, S2Blade, R3Blade, S3Blade)
MARKER_MONITORING= (S3Blade) %(R1Blade, S1Blade, R2Blade, S2Blade, R3Blade, S3Blade)
MARKER_ANALYZE_AVERAGE = AREA
%
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
%
% Courant-Friedrichs-Lewy condition of the finest grid
CFL_NUMBER= 20
%
% 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, 1.2, 5.0, 30.0) %(0.5, 1.05, 0.1, 1.0) %( 1.3, 1.2, 1.0, 10.0)
%
OBJECTIVE_FUNCTION= SURFACE_TOTAL_PRESSURE
OBJECTIVE_WEIGHT = 1.0
%
%
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
% Linear solver or smoother for implicit formulations
LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver (ILU, LU_SGS, LINELET, JACOBI)
LINEAR_SOLVER_PREC= LU_SGS
%
% Min error of the linear solver for the implicit formulation
LINEAR_SOLVER_ERROR= 1E-4
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 10
%
% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
% Coefficient for the limiter
VENKAT_LIMITER_COEFF= 0.01
%
% Freeze the value of the limiter after a number of iterations
LIMITER_ITER= 999999
%
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method
CONV_NUM_METHOD_FLOW= ROE %JST
ENTROPY_FIX_COEFF= 0.001
%
JST_SENSOR_COEFF= ( 0.5, 0.02 ) %( 0.5, 0.02 )
% Spatial numerical order integration
MUSCL_FLOW= NO %YES
%
% Slope limiter (VENKATAKRISHNAN, VAN_ALBADA)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_FLOW= EULER_IMPLICIT
%
% Use a Newton-Krylov method on the flow equations, see TestCases/rans/oneram6 turb_ONERAM6_nk.cfg
% For multizone discrete adjoint it will use FGMRES on inner iterations with restart frequency
% equal to "QUASI_NEWTON_NUM_SAMPLES".
%NEWTON_KRYLOV= YES
%
% 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= NO %YES
%
% Slope limiter (NONE, VENKATAKRISHNAN, BARTH_JESPERSEN, VAN_ALBADA_EDGE,
% SHARP_EDGES, WALL_DISTANCE)
%SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN
%
% Enable (if != 0) quasi-Newton acceleration/stabilization of discrete adjoints
%QUASI_NEWTON_NUM_SAMPLES= 20
%
% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
%
% Convective numerical method (SCALAR_UPWIND)
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
%
% Spatial numerical order integration
MUSCL_TURB= NO %YES
%
% Slope limiter (VENKATAKRISHNAN, MINMOD)
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
%
% Time discretization (EULER_IMPLICIT)
TIME_DISCRE_TURB= EULER_IMPLICIT
%
% Reduction factor of the CFL coefficient in the turbulence problem
CFL_REDUCTION_TURB= 0.1
%
% -------------------- 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_DEFINITION= (STATOR, -0.392, -0.014, 0.26, -0.267, -0.014, 0.26, -0.267, 0.017, 0.26, -0.392, 0.017, 0.26, -0.392, -0.014, 0.31, -0.267, -0.014, 0.31, -0.267, 0.017, 0.31, -0.392, 0.017, 0.31)
%
% FFD box degree: 3D case (x_degree, y_degree, z_degree)
% 2D case (x_degree, y_degree, 0)
FFD_DEGREE= (7, 2, 4)
%
% Surface continuity at the intersection with the FFD (1ST_DERIVATIVE, 2ND_DERIVATIVE)
FFD_CONTINUITY= 2ND_DERIVATIVE
%
% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
%
% Kind of deformation (NO_DEFORMATION, TRANSLATION, ROTATION, SCALE,
% FFD_SETTING, FFD_NACELLE
% FFD_CONTROL_POINT, FFD_CAMBER, FFD_THICKNESS, FFD_TWIST
% FFD_CONTROL_POINT_2D, FFD_CAMBER_2D, FFD_THICKNESS_2D, FFD_TWIST_2D,
% HICKS_HENNE, SURFACE_BUMP)
%DV_KIND= FFD_SETTING
%DV_KIND= FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT, FFD_CONTROL_POINT
% Marker of the surface in which we are going apply the shape deformation
%DV_MARKER= (S3Blade)
%
% Parameters of the shape deformation
%DV_PARAM= (STATOR, 0, 0, 0, 0.0, 1.0, 0.0 ); (STATOR, 1, 0, 0, 0.0, 1.0, 0.0 ); (STATOR, 2, 0, 0, 0.0, 1.0, 0.0 ); (STATOR, 3, 0, 0, 0.0, 1.0, 0.0 ); (STATOR, 4, 0, 0, 0.0, 1.0, 0.0 ); (STATOR, 5, 0, 0, 0.0, 1.0, 0.0 ); (STATOR, 6, 0, 0, 0.0, 1.0, 0.0 ); (STATOR, 7, 0, 0, 0.0, 1.0, 0.0 ); (STATOR, 0, 1, 0, 0.0, 1.0, 0.0 ); (STATOR, 1, 1, 0, 0.0, 1.0, 0.0 ); (STATOR, 2, 1, 0, 0.0, 1.0, 0.0 ); (STATOR, 3, 1, 0, 0.0, 1.0, 0.0 ); (STATOR, 4, 1, 0, 0.0, 1.0, 0.0 ); (STATOR, 5, 1, 0, 0.0, 1.0, 0.0 ); (STATOR, 6, 1, 0, 0.0, 1.0, 0.0 ); (STATOR, 7, 1, 0, 0.0, 1.0, 0.0 ); (STATOR, 0, 2, 0, 0.0, 1.0, 0.0 ); (STATOR, 1, 2, 0, 0.0, 1.0, 0.0 ); (STATOR, 2, 2, 0, 0.0, 1.0, 0.0 ); (STATOR, 3, 2, 0, 0.0, 1.0, 0.0 ); (STATOR, 4, 2, 0, 0.0, 1.0, 0.0 ); (STATOR, 5, 2, 0, 0.0, 1.0, 0.0 ); (STATOR, 6, 2, 0, 0.0, 1.0, 0.0 ); (STATOR, 7, 2, 0, 0.0, 1.0, 0.0 ); (STATOR, 0, 0, 1, 0.0, 1.0, 0.0 ); (STATOR, 1, 0, 1, 0.0, 1.0, 0.0 ); (STATOR, 2, 0, 1, 0.0, 1.0, 0.0 ); (STATOR, 3, 0, 1, 0.0, 1.0, 0.0 ); (STATOR, 4, 0, 1, 0.0, 1.0, 0.0 ); (STATOR, 5, 0, 1, 0.0, 1.0, 0.0 ); (STATOR, 6, 0, 1, 0.0, 1.0, 0.0 ); (STATOR, 7, 0, 1, 0.0, 1.0, 0.0 ); (STATOR, 0, 1, 1, 0.0, 1.0, 0.0 ); (STATOR, 1, 1, 1, 0.0, 1.0, 0.0 ); (STATOR, 2, 1, 1, 0.0, 1.0, 0.0 ); (STATOR, 3, 1, 1, 0.0, 1.0, 0.0 ); (STATOR, 4, 1, 1, 0.0, 1.0, 0.0 ); (STATOR, 5, 1, 1, 0.0, 1.0, 0.0 ); (STATOR, 6, 1, 1, 0.0, 1.0, 0.0 ); (STATOR, 7, 1, 1, 0.0, 1.0, 0.0 ); (STATOR, 0, 2, 1, 0.0, 1.0, 0.0 ); (STATOR, 1, 2, 1, 0.0, 1.0, 0.0 ); (STATOR, 2, 2, 1, 0.0, 1.0, 0.0 ); (STATOR, 3, 2, 1, 0.0, 1.0, 0.0 ); (STATOR, 4, 2, 1, 0.0, 1.0, 0.0 ); (STATOR, 5, 2, 1, 0.0, 1.0, 0.0 ); (STATOR, 6, 2, 1, 0.0, 1.0, 0.0 ); (STATOR, 7, 2, 1, 0.0, 1.0, 0.0 ); (STATOR, 0, 0, 2, 0.0, 1.0, 0.0 ); (STATOR, 1, 0, 2, 0.0, 1.0, 0.0 ); (STATOR, 2, 0, 2, 0.0, 1.0, 0.0 ); (STATOR, 3, 0, 2, 0.0, 1.0, 0.0 ); (STATOR, 4, 0, 2, 0.0, 1.0, 0.0 ); (STATOR, 5, 0, 2, 0.0, 1.0, 0.0 ); (STATOR, 6, 0, 2, 0.0, 1.0, 0.0 ); (STATOR, 7, 0, 2, 0.0, 1.0, 0.0 ); (STATOR, 0, 1, 2, 0.0, 1.0, 0.0 ); (STATOR, 1, 1, 2, 0.0, 1.0, 0.0 ); (STATOR, 2, 1, 2, 0.0, 1.0, 0.0 ); (STATOR, 3, 1, 2, 0.0, 1.0, 0.0 ); (STATOR, 4, 1, 2, 0.0, 1.0, 0.0 ); (STATOR, 5, 1, 2, 0.0, 1.0, 0.0 ); (STATOR, 6, 1, 2, 0.0, 1.0, 0.0 ); (STATOR, 7, 1, 2, 0.0, 1.0, 0.0 ); (STATOR, 0, 2, 2, 0.0, 1.0, 0.0 ); (STATOR, 1, 2, 2, 0.0, 1.0, 0.0 ); (STATOR, 2, 2, 2, 0.0, 1.0, 0.0 ); (STATOR, 3, 2, 2, 0.0, 1.0, 0.0 ); (STATOR, 4, 2, 2, 0.0, 1.0, 0.0 ); (STATOR, 5, 2, 2, 0.0, 1.0, 0.0 ); (STATOR, 6, 2, 2, 0.0, 1.0, 0.0 ); (STATOR, 7, 2, 2, 0.0, 1.0, 0.0 ); (STATOR, 0, 0, 3, 0.0, 1.0, 0.0 ); (STATOR, 1, 0, 3, 0.0, 1.0, 0.0 ); (STATOR, 2, 0, 3, 0.0, 1.0, 0.0 ); (STATOR, 3, 0, 3, 0.0, 1.0, 0.0 ); (STATOR, 4, 0, 3, 0.0, 1.0, 0.0 ); (STATOR, 5, 0, 3, 0.0, 1.0, 0.0 ); (STATOR, 6, 0, 3, 0.0, 1.0, 0.0 ); (STATOR, 7, 0, 3, 0.0, 1.0, 0.0 ); (STATOR, 0, 1, 3, 0.0, 1.0, 0.0 ); (STATOR, 1, 1, 3, 0.0, 1.0, 0.0 ); (STATOR, 2, 1, 3, 0.0, 1.0, 0.0 ); (STATOR, 3, 1, 3, 0.0, 1.0, 0.0 ); (STATOR, 4, 1, 3, 0.0, 1.0, 0.0 ); (STATOR, 5, 1, 3, 0.0, 1.0, 0.0 ); (STATOR, 6, 1, 3, 0.0, 1.0, 0.0 ); (STATOR, 7, 1, 3, 0.0, 1.0, 0.0 ); (STATOR, 0, 2, 3, 0.0, 1.0, 0.0 ); (STATOR, 1, 2, 3, 0.0, 1.0, 0.0 ); (STATOR, 2, 2, 3, 0.0, 1.0, 0.0 ); (STATOR, 3, 2, 3, 0.0, 1.0, 0.0 ); (STATOR, 4, 2, 3, 0.0, 1.0, 0.0 ); (STATOR, 5, 2, 3, 0.0, 1.0, 0.0 ); (STATOR, 6, 2, 3, 0.0, 1.0, 0.0 ); (STATOR, 7, 2, 3, 0.0, 1.0, 0.0 ); (STATOR, 0, 0, 4, 0.0, 1.0, 0.0 ); (STATOR, 1, 0, 4, 0.0, 1.0, 0.0 ); (STATOR, 2, 0, 4, 0.0, 1.0, 0.0 ); (STATOR, 3, 0, 4, 0.0, 1.0, 0.0 ); (STATOR, 4, 0, 4, 0.0, 1.0, 0.0 ); (STATOR, 5, 0, 4, 0.0, 1.0, 0.0 ); (STATOR, 6, 0, 4, 0.0, 1.0, 0.0 ); (STATOR, 7, 0, 4, 0.0, 1.0, 0.0 ); (STATOR, 0, 1, 4, 0.0, 1.0, 0.0 ); (STATOR, 1, 1, 4, 0.0, 1.0, 0.0 ); (STATOR, 2, 1, 4, 0.0, 1.0, 0.0 ); (STATOR, 3, 1, 4, 0.0, 1.0, 0.0 ); (STATOR, 4, 1, 4, 0.0, 1.0, 0.0 ); (STATOR, 5, 1, 4, 0.0, 1.0, 0.0 ); (STATOR, 6, 1, 4, 0.0, 1.0, 0.0 ); (STATOR, 7, 1, 4, 0.0, 1.0, 0.0 ); (STATOR, 0, 2, 4, 0.0, 1.0, 0.0 ); (STATOR, 1, 2, 4, 0.0, 1.0, 0.0 ); (STATOR, 2, 2, 4, 0.0, 1.0, 0.0 ); (STATOR, 3, 2, 4, 0.0, 1.0, 0.0 ); (STATOR, 4, 2, 4, 0.0, 1.0, 0.0 ); (STATOR, 5, 2, 4, 0.0, 1.0, 0.0 ); (STATOR, 6, 2, 4, 0.0, 1.0, 0.0 ); (STATOR, 7, 2, 4, 0.0, 1.0, 0.0 )
%
% Value of the shape deformation
%DV_VALUE= 0.01
%
% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
%
% Linear solver or smoother for implicit formulations (FGMRES, RESTARTED_FGMRES, BCGSTAB)
%DEFORM_LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver (ILU, LU_SGS, JACOBI)
%DEFORM_LINEAR_SOLVER_PREC= ILU
%
% Number of smoothing iterations for mesh deformation
%DEFORM_LINEAR_SOLVER_ITER= 1000
%
% Number of nonlinear deformation iterations (surface deformation increments)
%DEFORM_NONLINEAR_ITER= 1
%
% Minimum residual criteria for the linear solver convergence of grid deformation
%DEFORM_LINEAR_SOLVER_ERROR= 1E-14
%
% Print the residuals during mesh deformation to the console (YES, NO)
%DEFORM_CONSOLE_OUTPUT= YES
%
% Deformation coefficient (linear elasticity limits from -1.0 to 0.5, a larger
% value is also possible)
%DEFORM_COEFF = 0.0
%
% Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME,
% WALL_DISTANCE, CONSTANT_STIFFNESS)
%DEFORM_STIFFNESS_TYPE= WALL_DISTANCE
%
% Deform the grid only close to the surface. It is possible to specify how much
% of the volumetric grid is going to be deformed in meters or inches (1E6 by default)
%DEFORM_LIMIT = 1E6
% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
% Number of total iterations
OUTER_ITER=1 %500
%
% Convergence criteria (CAUCHY, RESIDUAL)
CONV_FIELD= (RMS_DENSITY[0] , RMS_MOMENTUM-X[0] , SURFACE_MASSFLOW[0])
%
% Min value of the residual (log10 of the residual)
CONV_RESIDUAL_MINVAL= -14
%
% Start convergence criteria at iteration number
CONV_STARTITER= 10
CONV_CAUCHY_ELEMS= 100
CONV_CAUCHY_EPS= 1E-6
%
% Screen output fields (use 'SU2_CFD -d <config_file>' to view list of available fields)
SCREEN_OUTPUT= (OUTER_ITER, RMS_DENSITY[0], RMS_DENSITY[1], RMS_DENSITY[2], RMS_MOMENTUM-X[0], RMS_MOMENTUM-Y[0], RMS_ENERGY[0], SURFACE_MASSFLOW[0], MassFlowOut_2[1])
%
% History output groups (use 'SU2_CFD -d <config_file>' to view list of available fields)
HISTORY_OUTPUT= (ITER, RMS_RES, TURBO_PERF)
%
% Volume output fields/groups (use 'SU2_CFD -d <config_file>' to view list of available fields)
VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, TURBOMACHINERY, RESIDUAL, LIMITER, VORTEX_IDENTIFICATION)
%
OUTPUT_FILES= (RESTART, PARAVIEW, SURFACE_PARAVIEW, PARAVIEW_MULTIBLOCK) %, CGNS SURFACE_CGNS, STL_ASCII)
%
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
% Mesh input file
MESH_FILENAME= Axi.su2
%
% Mesh input file format
MESH_FORMAT= SU2
%
% Mesh output file
MESH_OUT_FILENAME= Axial.su2
% Restart flow input file
SOLUTION_FILENAME= restart_flow.dat
%
% Restart adjoint input file
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
% Output file format
TABULAR_FORMAT= CSV %TECPLOT
% Output file convergence history (w/o extension)
CONV_FILENAME= history
%
% 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 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= 100
%
% Writing convergence history frequency
HISTORY_WRT_FREQ_OUTER= 1
WRT_ZONE_HIST = YES
Let me know if you need any further information
Desktop (please complete the following information):
Beta Was this translation helpful? Give feedback.
All reactions