More incompressible tutorials.

Author: economon

Inc_Laminar_Cavity/images/buoyancy_density.png

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+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%                                                                              %
+% SU2 configuration file                                                       %
+% Case description: Buoyancy-driven flow inside a cavity                       %
+% Author: Thomas D. Economon						       %
+% Date: 2018.06.10                                                             %
+% File Version 6.1.0 "Falcon"                                                  %
+%                                                                              %
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
+%
+% Physical governing equations (EULER, NAVIER_STOKES,
+%                               WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
+%                               POISSON_EQUATION)
+PHYSICAL_PROBLEM= NAVIER_STOKES
+%
+% Regime type (COMPRESSIBLE, INCOMPRESSIBLE, FREESURFACE)
+REGIME_TYPE= INCOMPRESSIBLE
+%
+% Specify turbulent model (NONE, SA, SA_NEG, SST)
+KIND_TURB_MODEL= NONE
+%
+% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
+MATH_PROBLEM= DIRECT
+%
+% Restart solution (NO, YES)
+RESTART_SOL= NO
+
+% ---------------- INCOMPRESSIBLE FLOW CONDITION DEFINITION -------------------%
+%
+% Density model within the incompressible flow solver.
+% Options are CONSTANT (default), BOUSSINESQ, or VARIABLE. If VARIABLE,
+% an appropriate fluid model must be selected.
+INC_DENSITY_MODEL= VARIABLE
+%
+% Solve the energy equation in the incompressible flow solver
+INC_ENERGY_EQUATION = YES
+%
+% Initial density for incompressible flows (1.2886 kg/m^3 by default)
+% Uncomment a density below for a desired Rayleigh number
+%INC_DENSITY_INIT= 0.00018903539834  % Ra ~ 1e3
+%INC_DENSITY_INIT= 0.00059778241716  % Ra ~ 1e4
+%INC_DENSITY_INIT= 0.00189035398341  % Ra ~ 1e5
+INC_DENSITY_INIT= 0.00597782417156  % Ra ~ 1e6
+%
+% Initial velocity for incompressible flows (1.0,0,0 m/s by default)
+INC_VELOCITY_INIT= ( 1.0, 0.0, 0.0 )
+%
+% Initial temperature for incompressible flows that include the
+% energy equation (288.15 K by default). Value is ignored if
+% INC_ENERGY_EQUATION is false.
+INC_TEMPERATURE_INIT= 288.15
+
+% ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
+%
+% Fluid model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS,
+%              CONSTANT_DENSITY, INC_IDEAL_GAS)
+FLUID_MODEL= INC_IDEAL_GAS
+%
+% Specific heat at constant pressure, Cp (1004.703 J/kg*K (air)).
+% Incompressible fluids with energy eqn. only (CONSTANT_DENSITY, INC_IDEAL_GAS).
+SPECIFIC_HEAT_CP= 1004.703
+%
+% Molecular weight for an incompressible ideal gas (28.96 g/mol (air) default)
+% Incompressible fluids with energy eqn. only (CONSTANT_DENSITY, INC_IDEAL_GAS).
+MOLECULAR_WEIGHT= 28.96
+
+% --------------------------- VISCOSITY MODEL ---------------------------------%
+%
+% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY).
+VISCOSITY_MODEL= CONSTANT_VISCOSITY
+%
+% Molecular Viscosity that would be constant (1.716E-5 by default)
+MU_CONSTANT= 1.716e-5
+
+% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
+%
+% Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL).
+CONDUCTIVITY_MODEL= CONSTANT_CONDUCTIVITY
+%
+% Molecular Thermal Conductivity that would be constant (0.0257 by default)
+KT_CONSTANT= 0.0246295028571
+
+% ----------------------- BODY FORCE DEFINITION -------------------------------%
+%
+% Apply a body force as a source term (NO, YES)
+BODY_FORCE= YES
+%
+% Vector of body force values (BodyForce_X, BodyForce_Y, BodyForce_Z)
+BODY_FORCE_VECTOR= ( 0.0, -9.81, 0.0 )
+
+% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
+%
+% Reference origin for moment computation
+REF_ORIGIN_MOMENT_X = 0.25
+REF_ORIGIN_MOMENT_Y = 0.00
+REF_ORIGIN_MOMENT_Z = 0.00
+%
+% Reference area for force coefficients (0 implies automatic calculation)
+REF_AREA= 1.0
+
+% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
+%
+% Navier-Stokes (no-slip), constant heat flux wall  marker(s) (NONE = no marker)
+% Format: ( marker name, constant heat flux (J/m^2), ... )
+MARKER_HEATFLUX= ( upper, 0.0, lower, 0.0 )
+%
+% Navier-Stokes (no-slip), isothermal wall marker(s) (NONE = no marker)
+% Format: ( marker name, constant wall temperature (K), ... )
+MARKER_ISOTHERMAL= ( left, 461.04, right, 115.26 )
+%
+% Marker(s) of the surface to be plotted or designed
+MARKER_PLOTTING= ( upper, left, right, lower )
+%
+% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
+MARKER_MONITORING= ( NONE )
+
+% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
+%
+% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
+NUM_METHOD_GRAD= GREEN_GAUSS
+%
+% Courant-Friedrichs-Lewy condition of the finest grid
+CFL_NUMBER= 50.0
+%
+% Adaptive CFL number (NO, YES)
+CFL_ADAPT= NO
+%
+% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
+%                                        CFL max value )
+CFL_ADAPT_PARAM= ( 1.5, 0.5, 15.0, 1e10)
+%
+% Maximum Delta Time in local time stepping simulations
+MAX_DELTA_TIME= 1E6
+%
+% Runge-Kutta alpha coefficients
+RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
+%
+% Number of total iterations
+EXT_ITER= 99999
+
+% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
+%
+% Linear solver for the implicit (or discrete adjoint) formulation (BCGSTAB, FGMRES)
+LINEAR_SOLVER= FGMRES
+%
+% Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS)
+LINEAR_SOLVER_PREC= ILU
+%
+% Linael solver ILU preconditioner fill-in level (0 by default)
+LINEAR_SOLVER_ILU_FILL_IN= 0
+%
+% Min error of the linear solver for the implicit formulation
+LINEAR_SOLVER_ERROR= 1E-15
+%
+% Max number of iterations of the linear solver for the implicit formulation
+LINEAR_SOLVER_ITER= 10
+
+% -------------------------- MULTIGRID PARAMETERS -----------------------------%
+%
+% Multi-Grid Levels (0 = no multi-grid)
+MGLEVEL= 2
+%
+% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
+MGCYCLE= V_CYCLE
+%
+% Multi-grid pre-smoothing level
+MG_PRE_SMOOTH= ( 1, 1, 1, 1 )
+%
+% Multi-grid post-smoothing level
+MG_POST_SMOOTH= ( 0, 0, 0, 0 )
+%
+% Jacobi implicit smoothing of the correction
+MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
+%
+% Damping factor for the residual restriction
+MG_DAMP_RESTRICTION= 0.8
+%
+% Damping factor for the correction prolongation
+MG_DAMP_PROLONGATION= 0.8
+
+% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
+%
+% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
+%                              TURKEL_PREC, MSW)
+CONV_NUM_METHOD_FLOW= FDS
+%
+% Monotonic Upwind Scheme for Conservation Laws (TVD) in the flow equations.
+%           Required for 2nd order upwind schemes (NO, YES)
+MUSCL_FLOW= YES
+%
+% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,
+%                BARTH_JESPERSEN, VAN_ALBADA_EDGE)
+SLOPE_LIMITER_FLOW= NONE
+%
+% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
+TIME_DISCRE_FLOW= EULER_IMPLICIT
+
+
+% --------------------------- CONVERGENCE PARAMETERS --------------------------%
+%
+% Convergence criteria (CAUCHY, RESIDUAL)
+CONV_CRITERIA= RESIDUAL
+%
+% Residual reduction (order of magnitude with respect to the initial value)
+RESIDUAL_REDUCTION= 8
+%
+% Min value of the residual (log10 of the residual)
+RESIDUAL_MINVAL= -12
+%
+% Start convergence criteria at iteration number
+STARTCONV_ITER= 10
+%
+% Number of elements to apply the criteria
+CAUCHY_ELEMS= 100
+%
+% Epsilon to control the series convergence
+CAUCHY_EPS= 1E-6
+%
+% Function to apply the criteria (LIFT, DRAG, NEARFIELD_PRESS, SENS_GEOMETRY, 
+% 	      	    		 SENS_MACH, DELTA_LIFT, DELTA_DRAG)
+CAUCHY_FUNC_FLOW= DRAG
+
+% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
+%
+% Mesh input file
+MESH_FILENAME= mesh_cavity_257x257.su2
+%
+% Mesh input file format (SU2, CGNS, NETCDF_ASCII)
+MESH_FORMAT= SU2
+%
+% Mesh output file
+MESH_OUT_FILENAME= mesh_out.su2
+%
+% Restart flow input file
+SOLUTION_FLOW_FILENAME= solution_flow.dat
+%
+% Restart adjoint input file
+SOLUTION_ADJ_FILENAME= solution_adj.dat
+%
+% Output file format (PARAVIEW, TECPLOT, STL)
+OUTPUT_FORMAT= PARAVIEW
+%
+% Output file convergence history (w/o extension) 
+CONV_FILENAME= history
+%
+% Output file restart flow
+RESTART_FLOW_FILENAME= restart_flow.dat
+%
+% Output file restart adjoint
+RESTART_ADJ_FILENAME= restart_adj.dat
+%
+% Output file flow (w/o extension) variables
+VOLUME_FLOW_FILENAME= flow
+%
+% Output file adjoint (w/o extension) variables
+VOLUME_ADJ_FILENAME= adjoint
+%
+% Output objective function gradient (using continuous adjoint)
+GRAD_OBJFUNC_FILENAME= of_grad.dat
+%
+% Output file surface flow coefficient (w/o extension)
+SURFACE_FLOW_FILENAME= surface_flow
+%
+% Output file surface adjoint coefficient (w/o extension)
+SURFACE_ADJ_FILENAME= surface_adjoint
+%
+% Writing solution file frequency
+WRT_SOL_FREQ= 100
+%
+% Writing convergence history frequency
+WRT_CON_FREQ= 1
+
+% ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------%
+%
+% Extract a slice using GEO_BOUNDS (works with 2D cartesian grids only)
+WRT_SLICE= YES
+%
+% Geometrical bounds (Y coordinate) for the wing geometry analysis or
+% fuselage evaluation (X coordinate).
+GEO_BOUNDS= ( 0.499, 0.501)