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talbringtalbring
committedJan 31, 2020
Merge branch 'feature_WND_io'
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‎Unsteady_NACA0012/images/Time_Dep_Drag.png

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‎Unsteady_NACA0012/images/airfoil.png

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‎Unsteady_NACA0012/images/airfoil_big.png

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‎Unsteady_NACA0012/images/flow1.png

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‎Unsteady_NACA0012/images/wndAvgCDlongRe3.png

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‎Unsteady_NACA0012/images/wndAvgCDshortRe3.png

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‎Unsteady_NACA0012/images/wndFcts.png

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‎Unsteady_NACA0012/restart_flow_00497.dat

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‎Unsteady_NACA0012/restart_flow_00498.dat

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‎Unsteady_NACA0012/restart_flow_00499.dat

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‎Unsteady_NACA0012/unsteady_naca0012.cfg

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Unsteady periodic detached NACA0012 simulation %
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% Author: Steffen Schotthöfer %
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% Institution: TU Kaiserslautern %
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% Date: Jan 21, 2020 %
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% File Version 7.0.1 "Blackbird" (or newer) %
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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, NS_PLASMA)
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%
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SOLVER= RANS
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%
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% Specify turbulent model (NONE, SA, SA_NEG, SST)
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KIND_TURB_MODEL= SA
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%
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% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
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MATH_PROBLEM= DIRECT
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%
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% ------------------------- UNSTEADY SIMULATION -------------------------------%
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%
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TIME_DOMAIN = YES
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%
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% Numerical Method for Unsteady simulation(NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER, DUAL_TIME_STEPPING-2ND_ORDER, TIME_SPECTRAL)
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TIME_MARCHING= DUAL_TIME_STEPPING-2ND_ORDER
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%
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% Time Step for dual time stepping simulations (s)
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TIME_STEP= 5e-4
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%
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% Maximum Number of physical time steps.
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TIME_ITER= 2200
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%
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% Number of internal iterations (dual time method)
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INNER_ITER= 50
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%
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% Restart after the transient phase has passed
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RESTART_SOL = YES
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%
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% Specify unsteady restart iter
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RESTART_ITER = 499
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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= 0.3
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%
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% Angle of attack (degrees, only for compressible flows)
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AOA= 17.0
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%
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% De-Dimensionalization
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REF_DIMENSIONALIZATION = DIMENSIONAL
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%
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% Free-stream temperature (288.15 K by default)
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FREESTREAM_TEMPERATURE= 293.0
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%
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% Reynolds number (non-dimensional, based on the free-stream values)
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REYNOLDS_NUMBER= 1e+3
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%
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% Reynolds length (1 m by default)
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REYNOLDS_LENGTH= 1.0
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%
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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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%
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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% Navier-Stokes wall boundary marker(s) (NONE = no marker)
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MARKER_HEATFLUX= ( airfoil, 0.0)
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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= ( airfoil )
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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= (airfoil)
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%
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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= 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= 20.0
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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, 1.0, 100.0 )
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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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%
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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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% 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= 5
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%
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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= JST
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%
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% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
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%
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% 1st, 2nd and 4th order artificial dissipation coefficients
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JST_SENSOR_COEFF= ( 0.5, 0.01 )
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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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% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
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%
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MUSCL_TURB= NO
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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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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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% Convergence criteria (CAUCHY, RESIDUAL)
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CONV_CRITERIA = RESIDUAL
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% Field to apply Cauchy Criterion to
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CONV_FIELD= REL_RMS_DENSITY
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% Min value of the residual (log10 of the residual)
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CONV_RESIDUAL_MINVAL= -3
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%
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%% Time convergence monitoring
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WINDOW_CAUCHY_CRIT = YES
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%
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% List of time convergence fields
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CONV_WINDOW_FIELD = (TAVG_DRAG, TAVG_LIFT)
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%
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% Time Convergence Monitoring starts at Iteration WINDOW_START_ITER + CONV_WINDOW_STARTITER
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CONV_WINDOW_STARTITER = 0
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%
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% Epsilon to control the series convergence
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CONV_WINDOW_CAUCHY_EPS = 1E-3
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%
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% Number of elements to apply the criteria
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CONV_WINDOW_CAUCHY_ELEMS = 10
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%
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% Starting iteration for windowed-time-averaging
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WINDOW_START_ITER = 500
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%
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% Window used for reverse sweep. Options (SQUARE, HANN, HANN_SQUARE, BUMP)
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WINDOW_FUNCTION = HANN_SQUARE
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%
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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HISTORY_WRT_FREQ_INNER=0
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SCREEN_WRT_FREQ_INNER =1
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%
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% Mesh input file
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MESH_FILENAME= unsteady_naca0012_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= restart_flow.dat
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%
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% Restart adjoint input file
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SOLUTION_ADJ_FILENAME= restart_adj.dat
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%
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% Output file format (PARAVIEW, TECPLOT, STL)
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TABULAR_FORMAT= TECPLOT
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%
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% Output file convergence history (w/o extension)
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CONV_FILENAME= 0_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 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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WRT_SOL_FREQ= 1
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%
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WRT_SOL_FREQ_DUALTIME= 1
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%
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% Writing convergence history frequency% Writing convergence history frequency (dual time, only written to screen)
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WRT_CON_FREQ_DUALTIME= 10
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WRT_CON_FREQ= 1
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WRT_CSV_SOL=NO
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%
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SCREEN_OUTPUT=(INNER_ITER, TIME_ITER, DRAG, LIFT, RMS_DENSITY, REL_RMS_DENSITY, CAUCHY_TAVG_DRAG, CAUCHY_TAVG_LIFT)
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HISTORY_OUTPUT=(ITER,REL_RMS_RES,RMS_RES, AERO_COEFF,TAVG_AERO_COEFF, CAUCHY)
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%

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