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Adding incompressible flow tutorial files
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‎incompressible_flow/Inc_Heated_Cylinders/cht_2d_3cylinders.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: 2D cylinder array with CHT couplings %
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% Author: O. Burghardt, T. Economon %
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% Institution: Chair for Scientific Computing, TU Kaiserslautern %
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% Date: August 8, 2019 %
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% File Version 6.0.1 "Falcon" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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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= MULTIPHYSICS
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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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%
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CONFIG_LIST= (flow_cylinder.cfg, solid_cylinder1.cfg, solid_cylinder2.cfg, solid_cylinder3.cfg)
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%
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%
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MARKER_ZONE_INTERFACE= (cylinder_outer1, cylinder_inner1, cylinder_outer2, cylinder_inner2, cylinder_outer3, cylinder_inner3)
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%
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%
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MARKER_CHT_INTERFACE= (cylinder_outer1, cylinder_inner1, cylinder_outer2, cylinder_inner2, cylinder_outer3, cylinder_inner3)
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%
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% Number of total iterations
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OUTER_ITER = 10000
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%
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% Mesh input file
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MESH_FILENAME= mesh_cht_3cyl.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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% Output file format
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OUTPUT_FILES= (RESTART, TECPLOT, PARAVIEW, SURFACE_TECPLOT, SURFACE_PARAVIEW)
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% These are just default parameters so that we can run SU2_DOT_AD, they have no physical meaning for this test case.
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% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
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%
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% Kind of deformation (NO_DEFORMATION, TRANSLATION, ROTATION, SCALE,
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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, FFD_TWIST_2D,
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% HICKS_HENNE, SURFACE_BUMP)
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DV_KIND= HICKS_HENNE
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%
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% Marker of the surface in which we are going apply the shape deformation
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DV_MARKER= (cylinder_outer1, cylinder_inner1, cylinder_outer2, cylinder_inner2, cylinder_outer3, cylinder_inner3)
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%
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% Parameters of the shape deformation
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% - NO_DEFORMATION ( 1.0 )
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% - TRANSLATION ( x_Disp, y_Disp, z_Disp ), as a unit vector
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% - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
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% - SCALE ( 1.0 )
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% - ANGLE_OF_ATTACK ( 1.0 )
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% - FFD_SETTING ( 1.0 )
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% - FFD_CONTROL_POINT ( FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Disp, y_Disp, z_Disp )
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% - FFD_NACELLE ( FFD_BoxTag, rho_Ind, theta_Ind, phi_Ind, rho_Disp, phi_Disp )
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% - FFD_GULL ( FFD_BoxTag, j_Ind )
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% - FFD_ANGLE_OF_ATTACK ( FFD_BoxTag, 1.0 )
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% - FFD_CAMBER ( FFD_BoxTag, i_Ind, j_Ind )
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% - FFD_THICKNESS ( FFD_BoxTag, i_Ind, j_Ind )
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% - FFD_TWIST ( FFD_BoxTag, j_Ind, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
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% - FFD_CONTROL_POINT_2D ( FFD_BoxTag, i_Ind, j_Ind, x_Disp, y_Disp )
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% - FFD_CAMBER_2D ( FFD_BoxTag, i_Ind )
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% - FFD_THICKNESS_2D ( FFD_BoxTag, i_Ind )
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% - FFD_TWIST_2D ( FFD_BoxTag, x_Orig, y_Orig )
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% - HICKS_HENNE ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), x_Loc )
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% - SURFACE_BUMP ( x_Start, x_End, x_Loc )
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DV_PARAM= (0.0, 0.5)
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%
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% Value of the shape deformation
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DV_VALUE= 0.1

‎incompressible_flow/Inc_Heated_Cylinders/flow_cylinder.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Steady incompressible laminar flow around heated cylinders %
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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= INC_NAVIER_STOKES
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%
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% If Navier-Stokes, kind of turbulent model (NONE, SA)
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KIND_TURB_MODEL= NONE
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%
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% Restart solution (NO, YES)
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RESTART_SOL= NO
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%
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% Objective function in gradient evaluation (DRAG, LIFT, SIDEFORCE, MOMENT_X,
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% MOMENT_Y, MOMENT_Z, EFFICIENCY,
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% EQUIVALENT_AREA, NEARFIELD_PRESSURE,
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% FORCE_X, FORCE_Y, FORCE_Z, THRUST,
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% TORQUE, TOTAL_HEATFLUX,
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% MAXIMUM_HEATFLUX, INVERSE_DESIGN_PRESSURE,
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% INVERSE_DESIGN_HEATFLUX, SURFACE_TOTAL_PRESSURE,
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% SURFACE_MASSFLOW, SURFACE_STATIC_PRESSURE, SURFACE_MACH)
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% For a weighted sum of objectives: separate by commas, add OBJECTIVE_WEIGHT and MARKER_MONITORING in matching order.
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OBJECTIVE_FUNCTION= TOTAL_HEATFLUX
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%
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% List of weighting values when using more than one OBJECTIVE_FUNCTION. Separate by commas and match with MARKER_MONITORING.
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OBJECTIVE_WEIGHT= 1.0
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%
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% Data written to history file
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HISTORY_OUTPUT= (ITER, RMS_RES, HEAT)
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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% Farfield boundary marker(s) (NONE = no marker)
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MARKER_FAR= ( farfield )
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%
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% Marker(s) of the surface to be plotted or designed
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MARKER_PLOTTING= (cylinder_outer1, cylinder_outer2, cylinder_outer3)
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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= (cylinder_outer1, cylinder_outer2, cylinder_outer3)
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% ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%
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%
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% Density model within the incompressible flow solver.
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% Options are CONSTANT (default), BOUSSINESQ, or VARIABLE. If VARIABLE,
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% an appropriate fluid model must be selected.
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INC_DENSITY_MODEL= VARIABLE
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%
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% Solve the energy equation in the incompressible flow solver
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INC_ENERGY_EQUATION = YES
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%
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% Initial density for incompressible flows (1.2886 kg/m^3 by default)
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INC_DENSITY_INIT= 0.000210322
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%
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% Initial velocity for incompressible flows (1.0,0,0 m/s by default)
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INC_VELOCITY_INIT= ( 3.40297, 0.0, 0.0 )
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%
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% Initial temperature for incompressible flows that include the
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% energy equation (288.15 K by default). Value is ignored if
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% INC_ENERGY_EQUATION is false.
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INC_TEMPERATURE_INIT= 288.15
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%
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% Non-dimensionalization scheme for incompressible flows. Options are
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% INITIAL_VALUES (default), REFERENCE_VALUES, or DIMENSIONAL.
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% INC_*_REF values are ignored unless REFERENCE_VALUES is chosen.
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INC_NONDIM= 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)
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FLUID_MODEL= INC_IDEAL_GAS
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%
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% Specific heat at constant pressure, Cp (1004.703 J/kg*K (air)).
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% Incompressible fluids with energy eqn. only (CONSTANT_DENSITY, INC_IDEAL_GAS).
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SPECIFIC_HEAT_CP= 1004.703
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%
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% Molecular weight for an incompressible ideal gas (28.96 g/mol (air) default)
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% Incompressible fluids with energy eqn. only (CONSTANT_DENSITY, INC_IDEAL_GAS).
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MOLECULAR_WEIGHT= 28.96
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% --------------------------- VISCOSITY MODEL ---------------------------------%
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%
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% Viscosity model (SUTHERLAND, CONSTANT_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= 1.7893e-05
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%
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% Sutherland Viscosity Ref (1.716E-5 default value for AIR SI)
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MU_REF= 1.716E-5
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%
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% Sutherland Temperature Ref (273.15 K default value for AIR SI)
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MU_T_REF= 273.15
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%
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% Sutherland constant (110.4 default value for AIR SI)
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SUTHERLAND_CONSTANT= 110.4
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% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
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%
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% Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL).
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CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
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%
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% Molecular Thermal Conductivity that would be constant (0.0257 by default)
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KT_CONSTANT= 0.0257
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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), only for CONSTANT_PRANDTL)
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PRANDTL_TURB= 0.90
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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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% Courant-Friedrichs-Lewy condition of the finest grid
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CFL_NUMBER= 10.0
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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= ( 1.5, 0.5, 10.0, 10000.0 )
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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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% ------------------------ 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= 1E-15
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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= 5
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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= FDS
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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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% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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% Min value of the residual (log10 of the residual)
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CONV_RESIDUAL_MINVAL= -19
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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-6
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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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 file convergence history (w/o extension)
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CONV_FILENAME= history
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%
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% Output file with the forces breakdown
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BREAKDOWN_FILENAME= forces_breakdown.dat
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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
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VALUE_OBJFUNC_FILENAME= of_eval.dat
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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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WRT_SOL_FREQ= 250
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%
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% Writing convergence history frequency
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WRT_CON_FREQ= 1
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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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% Number of smoothing iterations for mesh deformation
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DEFORM_LINEAR_SOLVER_ITER= 200
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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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% 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= INVERSE_VOLUME
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%
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% Visualize the deformation (NO, YES)
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VISUALIZE_VOLUME_DEF= YES

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