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new config file for CoolProp viscosity and conductivity model
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‎TestCases/nicf/coolprop/coolprop.cfg

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Supersonic flow over a wedge in a channel. %
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% Author: Thomas D. Economon %
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% Institution: Stanford University %
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% Date: 2012.10.07 %
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% File Version 5.0.0 "Raven" %
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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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% WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
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% POISSON_EQUATION)
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SOLVER= RANS
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KIND_TURB_MODEL= SA
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% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
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MATH_PROBLEM= DIRECT
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% Restart solution (NO, YES)
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RESTART_SOL= NO
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% ----------- COMPRESSIBLE AND INCOMPRESSIBLE 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= 2.5
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%
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% Angle of attack (degrees)
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AOA= 0.0
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%
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% Side-slip angle (degrees)
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SIDESLIP_ANGLE= 0.0
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%
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INIT_OPTION= REYNOLDS
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% Free-stream pressure (101325.0 N/m^2 by default, only Euler flows)
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%FREESTREAM_PRESSURE= 1e6
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%
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% Free-stream temperature (288.15 K by default)
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FREESTREAM_TEMPERATURE= 500
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REYNOLDS_NUMBER= 6e7
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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% Reference origin for moment computation
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REF_ORIGIN_MOMENT_X = 0.25
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REF_ORIGIN_MOMENT_Y = 0.00
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REF_ORIGIN_MOMENT_Z = 0.00
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%
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% Reference length for pitching, rolling, and yawing non-dimensional moment
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REF_LENGTH= 1.0
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%
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% Reference area for force coefficients (0 implies automatic calculation)
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REF_AREA= 1.0
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FLUID_MODEL= COOLPROP
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FLUID_NAME = Nitrogen
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VISCOSITY_MODEL= COOLPROP
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CONDUCTIVITY_MODEL= CONSTANT_COOLPROP
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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% Euler wall boundary marker(s) (NONE = no marker)
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MARKER_EULER= ( upper, lower )
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MARKER_RIEMANN= (inlet, STATIC_SUPERSONIC_INFLOW_PT, 1e6, 500, 2.5, 0.0, 0.0, outlet, STATIC_PRESSURE, 1e6, 0.0, 0.0, 0.0, 0.0)
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%MARKER_SUPERSONIC_INLET= ( inlet, 300.0, 100000.0, 695.4290761824674, 0.0, 0.0 )
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%MARKER_OUTLET= ( outlet, 10000.0 )
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%
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% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
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MARKER_MONITORING= ( upper, lower )
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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, LEAST_SQUARES,
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% WEIGHTED_LEAST_SQUARES)
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NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
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%
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% Courant-Friedrichs-Lewy condition of the finest grid
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CFL_NUMBER= 1.0
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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, 5.0, 1e10 )
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%
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% Runge-Kutta alpha coefficients
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RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
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%
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% Number of total iterations
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ITER= 5000
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%
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% Linear solver for the implicit formulation (BCGSTAB, FGMRES)
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LINEAR_SOLVER= FGMRES
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%
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% Preconditioner of the Krylov linear solver (ILU, JACOBI, LINELET, LU_SGS)
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LINEAR_SOLVER_PREC= ILU
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%
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% Min error of the linear solver for the implicit formulation
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LINEAR_SOLVER_ERROR= 1E-6
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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= 20
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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= W_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= 1.0
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%
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% Damping factor for the correction prolongation
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MG_DAMP_PROLONGATION= 1.0
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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, HLLC,
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% TURKEL_PREC, MSW)
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CONV_NUM_METHOD_FLOW= HLLC
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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 limiter (smooth regions)
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VENKAT_LIMITER_COEFF= 0.006
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%
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% 2nd and 4th order artificial dissipation coefficients
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JST_SENSOR_COEFF= ( 0.5, 0.02 )
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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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% Turbulene model
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CONV_NUM_METHOD_TURB= SCALAR_UPWIND
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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% Convergence criteria (CAUCHY, RESIDUAL)
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CONV_FIELD= RMS_DENSITY
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%
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% Min value of the residual (log10 of the residual)
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CONV_RESIDUAL_MINVAL= -20
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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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%
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% Number of elements to apply the criteria
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CONV_CAUCHY_ELEMS= 100
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%
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% Epsilon to control the series convergence
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CONV_CAUCHY_EPS= 1E-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= mesh.su2
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%
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% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
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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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% Restart adjoint input file
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SOLUTION_ADJ_FILENAME= solution_adj.dat
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%
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% Output tabular format (CSV, TECPLOT)
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TABULAR_FORMAT= CSV
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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 restart adjoint
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RESTART_ADJ_FILENAME= restart_adj.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 adjoint (w/o extension) variables
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VOLUME_ADJ_FILENAME= adjoint
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%
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% Output objective function gradient (using continuous adjoint)
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GRAD_OBJFUNC_FILENAME= of_grad.dat
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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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% Output file surface adjoint coefficient (w/o extension)
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SURFACE_ADJ_FILENAME= surface_adjoint
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%
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% Writing solution file frequency
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OUTPUT_WRT_FREQ= 10
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%
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% Writing convergence history frequency
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SCREEN_WRT_FREQ_INNER= 1
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%
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% Screen output
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SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG)
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% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
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%
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%
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% Kind of deformation (NO_DEFORMATION, SCALE_GRID, TRANSLATE_GRID, ROTATE_GRID,
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% FFD_SETTING, FFD_NACELLE,
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% FFD_CONTROL_POINT, FFD_CAMBER, FFD_THICKNESS, FFD_TWIST
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% FFD_CONTROL_POINT_2D, FFD_CAMBER_2D, FFD_THICKNESS_2D,
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% FFD_TWIST_2D, HICKS_HENNE, SURFACE_BUMP, SURFACE_FILE)
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DV_KIND= SCALE_GRID
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%
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% - NO_DEFORMATION ( 1.0 )
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% - TRANSLATE_GRID ( x_Disp, y_Disp, z_Disp ), as a unit vector
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% - ROTATE_GRID ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) axis, DV_VALUE in deg.
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% - SCALE_GRID ( 1.0 )
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DV_PARAM= ( 1.0 )
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%
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% Value of the deformation
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DV_VALUE= 10.0
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‎TestCases/nicf/coolprop/coolprop_nozzle.cfg

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This file was deleted.

‎TestCases/parallel_regression.py

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# Rarefaction Q1D nozzle coolprop_nozzle
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coolprop_nozzle = TestCase('coolprop_nozzle')
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coolprop_nozzle.cfg_dir = "nicf/coolprop"
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coolprop_nozzle.cfg_file = "coolprop_nozzle.cfg"
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coolprop_nozzle.cfg_file = "coolprop.cfg"
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coolprop_nozzle.test_iter = 10
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coolprop_nozzle.test_vals = [-4.692149, -1.965079, 3.428130, 0.000000, 0.000000]
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coolprop_nozzle.test_vals = [3.355600, 1.002021, 7.055921, -3.456001, 0.925622]
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test_list.append(coolprop_nozzle)
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######################################

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