Merge pull request #26 from su2code/develop

Develop

compressible_flow/Transitional_Flat_Plate/transitional_BC_model_ConfigFile.cfg

@@ -17,12 +17,11 @@
 %                               POISSON_EQUATION)
 SOLVER= INC_RANS
 %
-% Specify turbulent model (NONE, SA, SA_NEG, SST)
+% Specify turbulent model (NONE, SA, SST)
 KIND_TURB_MODEL= SA
-%
-% Specify transition model (NONE, LM, BC)
-KIND_TRANS_MODEL= BC
-FREESTREAM_TURBULENCEINTENSITY = 0.18
+SA_OPTIONS= BCM
+% Turbulence intensity I = u'/U
+FREESTREAM_TURBULENCEINTENSITY = 0.0018
 %
 % Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
 MATH_PROBLEM= DIRECT

compressible_flow/Unsteady_NACA0012/unsteady_naca0012.cfg

@@ -9,207 +9,114 @@
 %                                                                              %
 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 
-% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
+% SOLVER
 %
-% Physical governing equations (EULER, NAVIER_STOKES, NS_PLASMA)
-%                               
 SOLVER= RANS
-%
-% Specify turbulent model (NONE, SA, SA_NEG, SST)
 KIND_TURB_MODEL= SA
-%
-% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
+REF_DIMENSIONALIZATION= DIMENSIONAL
 MATH_PROBLEM= DIRECT
+
+% RESTART
 %
-% ------------------------- UNSTEADY SIMULATION -------------------------------%
-%
-TIME_DOMAIN = YES
-%
-% Numerical Method for Unsteady simulation(NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER, DUAL_TIME_STEPPING-2ND_ORDER, TIME_SPECTRAL)
-TIME_MARCHING= DUAL_TIME_STEPPING-2ND_ORDER
-%
-% Time Step for dual time stepping simulations (s)
-TIME_STEP= 5e-4
-%
-% Maximum Number of physical time steps.
-TIME_ITER= 2200
-%
-% Number of internal iterations (dual time method)
-INNER_ITER= 50
-%
-% Restart after the transient phase has passed
-RESTART_SOL = YES
-%
-% Specify unsteady restart iter
-RESTART_ITER = 499
-% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
+RESTART_SOL= YES
+RESTART_ITER= 499
+
+% COMPRESSIBLE FREE-STREAM
 %
-% Mach number (non-dimensional, based on the free-stream values)
 MACH_NUMBER= 0.3
-%
-% Angle of attack (degrees, only for compressible flows)
 AOA= 17.0
-%
-% De-Dimensionalization
-REF_DIMENSIONALIZATION = DIMENSIONAL
-%
-% Free-stream temperature (288.15 K by default)
 FREESTREAM_TEMPERATURE= 293.0
-%
-% Reynolds number (non-dimensional, based on the free-stream values)
-REYNOLDS_NUMBER= 1e+3
-%
-% Reynolds length (1 m by default)
+FREESTREAM_PRESSURE= 101325.0
+REYNOLDS_NUMBER= 1000.0
 REYNOLDS_LENGTH= 1.0
+
+% REFERENCE VALUES
 %
-% ---------------------- 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 length for pitching, rolling, and yawing non-dimensional moment
+REF_ORIGIN_MOMENT_X= 0.25
+REF_ORIGIN_MOMENT_Y= 0.00
+REF_ORIGIN_MOMENT_Z= 0.00
 REF_LENGTH= 1.0
-%
-% Reference area for force coefficients (0 implies automatic calculation)
 REF_AREA= 1.0
+
+% BOUNDARY CONDITIONS
 %
-% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
-%
-% Navier-Stokes wall boundary marker(s) (NONE = no marker)
-MARKER_HEATFLUX= ( airfoil, 0.0)
-%
-% Farfield boundary marker(s) (NONE = no marker)
-MARKER_FAR= ( farfield)
-%
-% Marker(s) of the surface to be plotted or designed
-MARKER_PLOTTING= (  airfoil )
-%
-% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated
-MARKER_MONITORING= (airfoil)
+MARKER_HEATFLUX= ( airfoil, 0.0 )
+MARKER_FAR= ( farfield )
+MARKER_PLOTTING= ( airfoil )
+MARKER_MONITORING= ( airfoil )
+
+% DISCRETIZATION
 %
-% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
+TIME_DOMAIN= YES
+TIME_MARCHING= DUAL_TIME_STEPPING-2ND_ORDER
+TIME_STEP= 5e-4
 %
-% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
 NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
-%
-% Courant-Friedrichs-Lewy condition of the finest grid
-CFL_NUMBER= 20.0
-%
-% 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, 1.0, 100.0 )
-%
-% Runge-Kutta alpha coefficients
-RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
-%
-%
-% Linear solver for the implicit formulation (BCGSTAB, FGMRES)
-LINEAR_SOLVER= FGMRES
-%
-% Min error of the linear solver for the implicit formulation
-LINEAR_SOLVER_ERROR= 1E-6
-%
-% Max number of iterations of the linear solver for the implicit formulation
-LINEAR_SOLVER_ITER= 5
-%
-% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
-%
-% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
-%                              TURKEL_PREC, MSW)
 CONV_NUM_METHOD_FLOW= JST
-%
-% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
-%
-% 1st, 2nd and 4th order artificial dissipation coefficients
-JST_SENSOR_COEFF= (  0.5, 0.01 )
-%
-% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
-TIME_DISCRE_FLOW= EULER_IMPLICIT
-%
-% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
-%
-% Convective numerical method (SCALAR_UPWIND)
+JST_SENSOR_COEFF= ( 0.5, 0.005 )
 CONV_NUM_METHOD_TURB= SCALAR_UPWIND
-%
-% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
-%
 MUSCL_TURB= NO
+
+% SOLUTION METHODS
 %
-% Time discretization (EULER_IMPLICIT)
+TIME_DISCRE_FLOW= EULER_IMPLICIT
 TIME_DISCRE_TURB= EULER_IMPLICIT
+CFL_NUMBER= 1e12
+CFL_ADAPT= NO
+LINEAR_SOLVER= FGMRES
+LINEAR_SOLVER_ERROR= 0.1
+LINEAR_SOLVER_ITER= 10
+
+% INNER CONVERGENCE
 %
-% --------------------------- CONVERGENCE PARAMETERS --------------------------%
-%
-% Field to apply Cauchy Criterion to
+INNER_ITER= 10
 CONV_FIELD= REL_RMS_DENSITY
-% Min value of the residual (log10 of the residual)
 CONV_RESIDUAL_MINVAL= -3
+CONV_STARTITER= 0
+
+% TIME CONVERGENCE
 %
-%% Time convergence monitoring
-WINDOW_CAUCHY_CRIT = YES
-%
-% List of time convergence fields 
-CONV_WINDOW_FIELD = (TAVG_DRAG, TAVG_LIFT)
+TIME_ITER= 2000
 %
-% Time Convergence Monitoring starts at Iteration WINDOW_START_ITER + CONV_WINDOW_STARTITER
-CONV_WINDOW_STARTITER = 0
+% Starting iteration and type for windowed-time-averaging
+WINDOW_CAUCHY_CRIT= YES
+WINDOW_START_ITER= 500
+WINDOW_FUNCTION= HANN_SQUARE
 %
+% Monitored fields
+CONV_WINDOW_FIELD= ( TAVG_DRAG, TAVG_LIFT )
+% Time Convergence monitoring starts at iteration WINDOW_START_ITER + CONV_WINDOW_STARTITER
+CONV_WINDOW_STARTITER= 0
 % Epsilon to control the series convergence
-CONV_WINDOW_CAUCHY_EPS = 1E-3
-%
+CONV_WINDOW_CAUCHY_EPS= 1E-4
 % Number of elements to apply the criteria
-CONV_WINDOW_CAUCHY_ELEMS = 10
-%
-% Starting iteration for windowed-time-averaging
-WINDOW_START_ITER = 500
-%
-% Window used for reverse sweep. Options (SQUARE, HANN, HANN_SQUARE, BUMP)
-WINDOW_FUNCTION = HANN_SQUARE
-%
-% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
+CONV_WINDOW_CAUCHY_ELEMS= 10
+
+% INPUT/OUTPUT
 %
-HISTORY_WRT_FREQ_INNER=0
-SCREEN_WRT_FREQ_INNER =1
+HISTORY_WRT_FREQ_INNER= 0
+SCREEN_WRT_FREQ_INNER= 100
 %
 % Mesh input file
 MESH_FILENAME= unsteady_naca0012_mesh.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
+% Restart input files
 SOLUTION_FILENAME= restart_flow.dat
-%
-% Restart adjoint input file
 SOLUTION_ADJ_FILENAME= restart_adj.dat
 %
-% Output file format (PARAVIEW, TECPLOT, STL)
-TABULAR_FORMAT= TECPLOT
-%
-% Output file convergence history (w/o extension) 
-CONV_FILENAME= 0_history
-%
-% Output file restart flow
+% Output restart files
 RESTART_FILENAME= restart_flow.dat
-%
-% Output file restart adjoint
 RESTART_ADJ_FILENAME= restart_adj.dat
 %
-% Output file flow (w/o extension) variables
+% Output file names
 VOLUME_FILENAME= flow
-%
-% Output file surface flow coefficient (w/o extension)
 SURFACE_FILENAME= surface_flow
+TABULAR_FORMAT= CSV
+CONV_FILENAME= history
 %
+SCREEN_OUTPUT= ( TIME_ITER, INNER_ITER, RMS_DENSITY, REL_RMS_DENSITY, DRAG, LIFT, CAUCHY_TAVG_DRAG, CAUCHY_TAVG_LIFT )
+HISTORY_OUTPUT= ( TIME_ITER, INNER_ITER, REL_RMS_RES, RMS_RES, AERO_COEFF, TAVG_AERO_COEFF, CAUCHY )
 %
-SCREEN_OUTPUT=(TIME_ITER, INNER_ITER, DRAG, LIFT, RMS_DENSITY, REL_RMS_DENSITY,  CAUCHY_TAVG_DRAG, CAUCHY_TAVG_LIFT)
-HISTORY_OUTPUT=(ITER,REL_RMS_RES,RMS_RES, AERO_COEFF,TAVG_AERO_COEFF, CAUCHY)
-%
+OUTPUT_FILES= ( RESTART, PARAVIEW )
+OUTPUT_WRT_FREQ= ( 1, 1 )