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add test case and regression list entry
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‎TestCases/axisymmetric_rans/air_nozzle/air_nozzle.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Axisymmetric supersonic converging-diverging air nozzle %
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% Author: Florian Dittmann %
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% Date: 2021.12.02 %
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% File Version 7.10 "Blackbird" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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%
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% Physical governing equations (EULER, NAVIER_STOKES,
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% FEM_EULER, FEM_NAVIER_STOKES, FEM_RANS, FEM_LES,
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% WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
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% POISSON_EQUATION)
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SOLVER= RANS
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%
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% Specify turbulence model (NONE, SA, SA_NEG, SST, SA_E, SA_COMP, SA_E_COMP)
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KIND_TURB_MODEL= SST
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%
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% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT, DISCRETE_ADJOINT)
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MATH_PROBLEM= DIRECT
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%
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% Restart solution (NO, YES)
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RESTART_SOL= YES
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%
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% System of measurements (SI, US)
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% International system of units (SI): ( meters, kilograms, Kelvins,
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% Newtons = kg m/s^2, Pascals = N/m^2,
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% Density = kg/m^3, Speed = m/s,
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% Equiv. Area = m^2 )
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% United States customary units (US): ( inches, slug, Rankines, lbf = slug ft/s^2,
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% psf = lbf/ft^2, Density = slug/ft^3,
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% Speed = ft/s, Equiv. Area = ft^2 )
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SYSTEM_MEASUREMENTS= SI
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%
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AXISYMMETRIC= YES
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%
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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%
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% Mach number (non-dimensional, based on the free-stream values)
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MACH_NUMBER= 1E-9
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%
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% Angle of attack (degrees, only for compressible flows)
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AOA= 0.0
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%
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% Side-slip angle (degrees, only for compressible flows)
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SIDESLIP_ANGLE= 0.0
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%
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% Init option to choose between Reynolds (default) or thermodynamics quantities
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% for initializing the solution (REYNOLDS, TD_CONDITIONS)
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INIT_OPTION= TD_CONDITIONS
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%
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% Free-stream option to choose between density and temperature (default) for
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% initializing the solution (TEMPERATURE_FS, DENSITY_FS)
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FREESTREAM_OPTION= TEMPERATURE_FS
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%
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% Free-stream pressure (101325.0 N/m^2, 2116.216 psf by default)
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FREESTREAM_PRESSURE= 1400000
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%
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% Free-stream temperature (288.15 K, 518.67 R by default)
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FREESTREAM_TEMPERATURE= 373.15
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%
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% Compressible flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
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% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
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REF_DIMENSIONALIZATION= DIMENSIONAL
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% ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
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%
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% Fluid model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS,
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% CONSTANT_DENSITY, INC_IDEAL_GAS, INC_IDEAL_GAS_POLY)
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FLUID_MODEL= STANDARD_AIR
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% --------------------------- VISCOSITY MODEL ---------------------------------%
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%
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% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY, POLYNOMIAL_VISCOSITY).
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VISCOSITY_MODEL= CONSTANT_VISCOSITY
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%
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% Molecular Viscosity that would be constant (1.716E-5 by default)
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MU_CONSTANT= 1.716E-5
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% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
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%
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% Laminar Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL,
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% POLYNOMIAL_CONDUCTIVITY).
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CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
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%
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% Laminar Prandtl number (0.72 (air), only for CONSTANT_PRANDTL)
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PRANDTL_LAM= 0.72
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%
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% Turbulent Prandtl number (0.9 (air) by default)
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PRANDTL_TURB= 0.90
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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% Navier-Stokes (no-slip), constant heat flux wall marker(s) (NONE = no marker)
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% Format: ( marker name, constant heat flux (J/m^2), ... )
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MARKER_HEATFLUX= ( WALL, 0.0 )
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%
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% Symmetry boundary marker(s) (NONE = no marker)
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MARKER_SYM= ( SYMMETRY )
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%
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% Riemann boundary marker(s) (NONE = no marker)
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% Format: (marker, data kind flag, list of data)
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MARKER_RIEMANN= ( INFLOW, TOTAL_CONDITIONS_PT, 1400000.0, 373.15, 1.0, 0.0, 0.0, OUTFLOW, STATIC_PRESSURE, 100000.0, 0.0, 0.0, 0.0, 0.0 )
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
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NUM_METHOD_GRAD= GREEN_GAUSS
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%
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% CFL number (initial value for the adaptive CFL number)
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CFL_NUMBER= 1000.0
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%
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% Adaptive CFL number (NO, YES)
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CFL_ADAPT= NO
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%
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% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
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% CFL max value )
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CFL_ADAPT_PARAM= ( 0.1, 2.0, 10.0, 1000.0 )
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%
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% Maximum Delta Time in local time stepping simulations
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MAX_DELTA_TIME= 1E6
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% ----------- SLOPE LIMITER AND DISSIPATION SENSOR DEFINITION -----------------%
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%
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% Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations.
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% Required for 2nd order upwind schemes (NO, YES)
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MUSCL_FLOW= YES
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%
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% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,
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% BARTH_JESPERSEN, VAN_ALBADA_EDGE)
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SLOPE_LIMITER_FLOW= NONE
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%
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%Coefficient for the Venkat's limiter (upwind scheme). A larger values decrease
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% the extent of limiting, values approaching zero cause
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% lower-order approximation to the solution (0.05 by default)
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VENKAT_LIMITER_COEFF= 0.05
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%
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% Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations.
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% Required for 2nd order upwind schemes (NO, YES)
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MUSCL_TURB= NO
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% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
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%
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% Linear solver or smoother for implicit formulations (BCGSTAB, FGMRES, SMOOTHER_JACOBI,
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% SMOOTHER_ILU, SMOOTHER_LUSGS,
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% SMOOTHER_LINELET)
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LINEAR_SOLVER= FGMRES
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%
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% Preconditioner of the Krylov linear solver (ILU, LU_SGS, LINELET, JACOBI)
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LINEAR_SOLVER_PREC= ILU
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%
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% Linael solver ILU preconditioner fill-in level (0 by default)
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LINEAR_SOLVER_ILU_FILL_IN= 0
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%
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% Minimum error of the linear solver for implicit formulations
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LINEAR_SOLVER_ERROR= 0.01
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%
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% Max number of iterations of the linear solver for the implicit formulation
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LINEAR_SOLVER_ITER= 10
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% -------------------------- MULTIGRID PARAMETERS -----------------------------%
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%
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% Multi-grid levels (0 = no multi-grid)
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MGLEVEL= 0
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%
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% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
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MGCYCLE= V_CYCLE
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%
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% Multi-grid pre-smoothing level
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MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
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%
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% Multi-grid post-smoothing level
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MG_POST_SMOOTH= ( 0, 0, 0, 0 )
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%
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% Jacobi implicit smoothing of the correction
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MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
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%
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% Damping factor for the residual restriction
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MG_DAMP_RESTRICTION= 0.75
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%
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% Damping factor for the correction prolongation
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MG_DAMP_PROLONGATION= 0.75
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, AUSMPLUSUP, AUSMPLUSUP2, HLLC,
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% TURKEL_PREC, MSW, FDS)
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CONV_NUM_METHOD_FLOW= ROE
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%
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% Entropy fix coefficient (0.0 implies no entropy fixing, 1.0 implies scalar
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% artificial dissipation)
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ENTROPY_FIX_COEFF= 0.1
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%
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% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
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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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% Convective numerical method (SCALAR_UPWIND)
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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%
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% Time discretization (EULER_IMPLICIT)
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TIME_DISCRE_TURB= EULER_IMPLICIT
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%
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% Reduction factor of the CFL coefficient in the turbulence problem
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CFL_REDUCTION_TURB= 1.0
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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% Number of total iterations
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ITER= 1000
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%
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% Convergence criteria (CAUCHY, RESIDUAL)
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CONV_CRITERIA= RESIDUAL
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%
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% Min value of the residual (log10 of the residual)
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CONV_RESIDUAL_MINVAL= -12
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%
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% Start convergence criteria at iteration number
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CONV_STARTITER= 10
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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% Mesh input file
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MESH_FILENAME= nozzle.su2
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%
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% Mesh input file format (SU2, CGNS)
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MESH_FORMAT= SU2
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%
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% Mesh output file
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MESH_OUT_FILENAME= mesh_out.su2
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%
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% Restart flow input file
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SOLUTION_FILENAME= solution_flow.dat
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%
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% Output file convergence history (w/o extension)
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CONV_FILENAME= history
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%
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% Output file restart flow
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RESTART_FILENAME= restart_flow.dat
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%
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% Output file flow (w/o extension) variables
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VOLUME_FILENAME= flow
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%
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% Output file surface flow coefficient (w/o extension)
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SURFACE_FILENAME= surface_flow
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%
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% Writing solution file frequency
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OUTPUT_WRT_FREQ= 1000
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%
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% Screen output
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SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_ENERGY, RMS_TKE, RMS_DISSIPATION)

‎TestCases/hybrid_regression.py‎

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propeller.test_vals = [-3.389576, -8.409529, 0.000048, 0.056329]
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test_list.append(propeller)
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#######################################
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### Axisymmetric Compressible RANS ###
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#######################################
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# Axisymmetric air nozzle (transonic)
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axi_rans_air_nozzle = TestCase('axi_rans_air_nozzle')
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axi_rans_air_nozzle.cfg_dir = "axisymmetric_rans/air_nozzle"
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axi_rans_air_nozzle.cfg_file = "air_nozzle.cfg"
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axi_rans_air_nozzle.test_iter = 10
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axi_rans_air_nozzle.test_vals = [-12.094937, -6.622043, -8.814412, -2.393288]
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test_list.append(axi_rans_air_nozzle)
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#################################
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## Compressible RANS Restart ###
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#################################

‎TestCases/parallel_regression.py‎

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propeller.tol = 0.00001
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test_list.append(propeller)
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#######################################
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### Axisymmetric Compressible RANS ###
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#######################################
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# Axisymmetric air nozzle (transonic)
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axi_rans_air_nozzle = TestCase('axi_rans_air_nozzle')
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axi_rans_air_nozzle.cfg_dir = "axisymmetric_rans/air_nozzle"
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axi_rans_air_nozzle.cfg_file = "air_nozzle.cfg"
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axi_rans_air_nozzle.test_iter = 10
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axi_rans_air_nozzle.test_vals = [ -12.096569, -6.625843, -8.807541, -2.393279]
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axi_rans_air_nozzle.su2_exec = "mpirun -n 2 SU2_CFD"
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axi_rans_air_nozzle.timeout = 1600
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axi_rans_air_nozzle.tol = 0.0001
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test_list.append(axi_rans_air_nozzle)
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#################################
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## Compressible RANS Restart ###
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#################################

‎TestCases/serial_regression.py‎

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propeller.tol = 0.00001
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test_list.append(propeller)
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#######################################
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### Axisymmetric Compressible RANS ###
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#######################################
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# Axisymmetric air nozzle (transonic)
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axi_rans_air_nozzle = TestCase('axi_rans_air_nozzle')
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axi_rans_air_nozzle.cfg_dir = "axisymmetric_rans/air_nozzle"
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axi_rans_air_nozzle.cfg_file = "air_nozzle.cfg"
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axi_rans_air_nozzle.test_iter = 10
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axi_rans_air_nozzle.test_vals = [ -12.093130, -6.619801, -8.806060, -2.393278]
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axi_rans_air_nozzle.su2_exec = "SU2_CFD"
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axi_rans_air_nozzle.timeout = 1600
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axi_rans_air_nozzle.tol = 0.0001
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test_list.append(axi_rans_air_nozzle)
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#################################
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## Compressible RANS Restart ###
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#################################

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