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Added fluid interface testcases
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‎TestCases/disc_adj_ffi/mixing_plane/circles.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: 2D Cylinder Interface (Mixing Plane) %
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% Author: J. Kelly %
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% Institution: University of Liverpool %
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% Date: Dec 1st, 2025 %
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% File Version 8.3.0 "Harrier" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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%
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MULTIZONE= YES
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CONFIG_LIST= (zone_1.cfg, zone_2.cfg)
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%
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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%
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SOLVER= RANS
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KIND_TURB_MODEL= SA
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READ_BINARY_RESTART=NO
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MATH_PROBLEM= DISCRETE_ADJOINT
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%
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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%
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MACH_NUMBER= 0.05
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AOA= 0.0
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FREESTREAM_PRESSURE= 1E6
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FREESTREAM_TEMPERATURE= 300.0
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FREESTREAM_DENSITY= 1.7418
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FREESTREAM_OPTION= TEMPERATURE_FS
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FREESTREAM_TURBULENCEINTENSITY = 0.03
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FREESTREAM_TURB2LAMVISCRATIO = 100.0
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INIT_OPTION= TD_CONDITIONS
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%
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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REF_ORIGIN_MOMENT_X = 0.00
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REF_ORIGIN_MOMENT_Y = 0.00
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REF_ORIGIN_MOMENT_Z = 0.00
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REF_LENGTH= 1.0
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REF_AREA= 1.0
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REF_DIMENSIONALIZATION= DIMENSIONAL
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%
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% ------------------------------ EQUATION OF STATE ----------------------------%
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%
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FLUID_MODEL= IDEAL_GAS
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GAMMA_VALUE= 1.4
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GAS_CONSTANT= 287.058
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%
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% --------------------------- VISCOSITY MODEL ---------------------------------%
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%
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VISCOSITY_MODEL= CONSTANT_VISCOSITY
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MU_REF= 1.716E-5
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MU_T_REF= 273.15
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SUTHERLAND_CONSTANT= 110.4
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%
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% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
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%
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CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
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%
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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%MARKER_EULER = (INFLOW, INMIX, OUTMIX, OUTFLOW, CIRC1, CIRC2)
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MARKER_HEATFLUX= ( CIRC1, 0.0, CIRC2, 0.0)
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%
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MARKER_PERIODIC= ( PER1, PER2, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 20.0, 0.0, PER3, PER4, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 20.0, 0.0)
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%
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%-------- INFLOW/OUTFLOW BOUNDARY CONDITION SPECIFIC FOR TURBOMACHINERY --------%
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%
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% 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)
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MARKER_TURBOMACHINERY= (INFLOW, OUTMIX, INMIX, OUTFLOW)
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%
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MARKER_ZONE_INTERFACE= (OUTMIX, INMIX)
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% Mixing-plane interface markers must be specified to activate the transfer of information between zones
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MARKER_MIXINGPLANE_INTERFACE= (OUTMIX, INMIX)
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%
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MARKER_GILES= (INFLOW, TOTAL_CONDITIONS_PT, 1E6, 300, 1.0, 0.0, 0.0,1.0,1.0, OUTMIX, MIXING_OUT, 0.0, 0.0, 0.0, 0.0, 0.0,1.0,1.0, INMIX, MIXING_IN, 0.0, 0.0, 0.0, 0.0, 0.0,1.0, 1.0, OUTFLOW, STATIC_PRESSURE, 9E5, 0.0, 0.0, 0.0, 0.0,1.0,1.0)
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SPATIAL_FOURIER= YES
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%
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%
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%---------------------------- TURBOMACHINERY SIMULATION -----------------------------%
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%
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TURBOMACHINERY_KIND= AXIAL AXIAL
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TURBO_PERF_KIND = TURBINE TURBINE
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TURBULENT_MIXINGPLANE= YES
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AVERAGE_PROCESS_KIND= MIXEDOUT
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PERFORMANCE_AVERAGE_PROCESS_KIND= MIXEDOUT
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MIXEDOUT_COEFF= (1.0, 1.0E-05, 15)
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AVERAGE_MACH_LIMIT= 0.05
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%
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% ------------------------ SURFACES IDENTIFICATION ----------------------------%
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%
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MARKER_PLOTTING= CIRC1, CIRC2
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MARKER_MONITORING= CIRC1, CIRC2
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MARKER_DESIGNING= CIRC1, CIRC2
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MARKER_ANALYZE= CIRC1, CIRC2
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%
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
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CFL_NUMBER= 10.0
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CFL_ADAPT= NO
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CFL_ADAPT_PARAM= ( 1.3, 1.2, 1.0, 10.0)
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%
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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%
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LINEAR_SOLVER= FGMRES
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LINEAR_SOLVER_PREC= LU_SGS
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LINEAR_SOLVER_ERROR= 1E-4
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LINEAR_SOLVER_ITER= 20
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%
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% ---------- NOT WORKING WITH PERIODIC BOUNDARY CONDITIONS !!!!! --------------%
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%
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%
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% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
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%
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VENKAT_LIMITER_COEFF= 0.05
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LIMITER_ITER= 999999
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%
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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CONV_NUM_METHOD_FLOW= ROE
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MUSCL_FLOW= NO
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SLOPE_LIMITER_FLOW= VAN_ALBADA_EDGE
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ENTROPY_FIX_COEFF= 0.1
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JST_SENSOR_COEFF= ( 0.5, 0.02 )
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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%
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% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
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%
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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MUSCL_TURB= NO
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SLOPE_LIMITER_TURB= VENKATAKRISHNAN
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TIME_DISCRE_TURB= EULER_IMPLICIT
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CFL_REDUCTION_TURB= 1.0
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%
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% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
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%
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%DV_KIND= FFD_SETTING
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%DV_MARKER= (CIRC1, CIRC2)
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%DV_PARAM= ( CIRC1, 1, 0, 0, 0.0, 1.0, 0.0 )
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%DV_VALUE= 0.001
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%
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DV_KIND= FFD_CONTROL_POINT_2D, FFD_CONTROL_POINT_2D, FFD_CONTROL_POINT_2D, FFD_CONTROL_POINT_2D
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DV_MARKER= ( CIRC1, CIRC2 )
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DV_PARAM=( CIRCLE1, 0, 0, 1.0, 0.0 );( CIRCLE2, 0, 0, 1.0, 0.0 );( CIRCLE1, 1, 1, 1.0, 0.0 );( CIRCLE2, 1, 1, 1.0, 0.0 )
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DV_VALUE=0.0,0.0,0.0,0.0
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%
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% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
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%
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% Linear solver or smoother for implicit formulations (FGMRES, RESTARTED_FGMRES, BCGSTAB)
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DEFORM_LINEAR_SOLVER= FGMRES
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%
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% Preconditioner of the Krylov linear solver (ILU, LU_SGS, JACOBI)
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DEFORM_LINEAR_SOLVER_PREC= ILU
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%
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% Number of smoothing iterations for mesh deformation
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DEFORM_LINEAR_SOLVER_ITER= 1000
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%
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% Number of nonlinear deformation iterations (surface deformation increments)
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DEFORM_NONLINEAR_ITER= 1
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%
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% Minimum residual criteria for the linear solver convergence of grid deformation
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DEFORM_LINEAR_SOLVER_ERROR= 1E-14
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%
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% Print the residuals during mesh deformation to the console (YES, NO)
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DEFORM_CONSOLE_OUTPUT= YES
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%
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% Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME,
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% WALL_DISTANCE, CONSTANT_STIFFNESS)
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DEFORM_STIFFNESS_TYPE= WALL_DISTANCE
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%
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%
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% -------------------- FREE-FORM DEFORMATION PARAMETERS -----------------------%
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%
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FFD_TOLERANCE= 1E-10
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FFD_ITERATIONS= 500
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FFD_DEFINITION= (CIRCLE1, -2.0, -2.0, 0.0, 2.0, -2.0, 0.0, 2.0, 2.0, 0.0, -2.0, 2.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0); (CIRCLE2, 18.0, -2.0, 0.0, 22.0, -2.0, 0.0, 22.0, 2.0, 0.0, 18.0, 2.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0)
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FFD_DEGREE= ( 2 , 2 , 0 ); (2, 2, 0)
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FFD_CONTINUITY= 2ND_DERIVATIVE
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%
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% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
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%
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% FFD_CONTROL_POINT_2D
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DEFINITION_DV= ( 19, 1.0 | CIRC1 | CIRCLE1, 0, 0, 1.0, 0.0 ); ( 19, 1.0 | CIRC2 | CIRCLE2, 0, 0, 1.0, 0.0 ); ( 19, 1.0 | CIRC1 | CIRCLE1, 1, 1, 1.0, 0.0 ); ( 19, 1.0 | CIRC2 | CIRCLE2, 1, 1, 1.0, 0.0 );
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OPT_OBJECTIVE= ENTROPY_GENERATION* 0.0001
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OPT_ITERATIONS= 19
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OPT_ACCURACY= 1E-10
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%
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% --------------------- OBJECTIVE FUNCTION DEFINITION -----------------------%
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%
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OBJECTIVE_FUNCTION= ENTROPY_GENERATION
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%
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% ------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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OUTER_ITER= 201
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CONV_RESIDUAL_MINVAL= -16
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CONV_STARTITER= 10
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CONV_CAUCHY_ELEMS= 100
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CONV_CAUCHY_EPS= 1E-6
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%
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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SCREEN_OUTPUT= OUTER_ITER, AVG_BGS_RES[0], AVG_BGS_RES[1], RMS_DENSITY[0], RMS_ENERGY[0], RMS_DENSITY[1], RMS_ENERGY[1], COMBO
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HISTORY_OUTPUT= ITER, RMS_RES, COMBO
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MESH_FILENAME= circ_out.su2
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MESH_FORMAT= SU2
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MESH_OUT_FILENAME= mesh_out.su2
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SOLUTION_FILENAME= solution_flow
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SOLUTION_ADJ_FILENAME= solution_adj
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TABULAR_FORMAT= CSV
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OUTPUT_FILES= RESTART_ASCII, TECPLOT, SURFACE_TECPLOT
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CONV_FILENAME= history
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RESTART_FILENAME= restart_flow
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RESTART_ADJ_FILENAME= restart_adj
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VOLUME_FILENAME= flow
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VOLUME_ADJ_FILENAME= adjoint
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GRAD_OBJFUNC_FILENAME= of_grad.dat
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SURFACE_FILENAME= surface_flow
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SURFACE_ADJ_FILENAME= surface_adjoint
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SURFACE_SENS_FILENAME= surface_sens
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WRT_ZONE_CONV= NO
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WRT_ZONE_HIST= YES
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OUTPUT_PRECISION= 16

‎TestCases/disc_adj_ffi/mixing_plane/zone_1.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: 2D Cylinder Interface (Mixing Plane) %
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% Author: J. Kelly %
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% Institution: University of Liverpool %
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% Date: Dec 1st, 2025 %
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% File Version 8.3.0 "Harrier" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
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%
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GRID_MOVEMENT= STEADY_TRANSLATION
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MACH_MOTION= 0.35
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TRANSLATION_RATE= 0.0 0.0 0.0

‎TestCases/disc_adj_ffi/mixing_plane/zone_2.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: 2D Cylinder Interface (Mixing Plane) %
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% Author: J. Kelly %
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% Institution: University of Liverpool %
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% Date: Dec 1st, 2025 %
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% File Version 8.3.0 "Harrier" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
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%
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GRID_MOVEMENT= STEADY_TRANSLATION
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MACH_MOTION= 0.35
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TRANSLATION_RATE= 0.0 0.0 0.0

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