- Remove unecessary comments from config files

Author: rois1995

TestCases/transition/E387_Airfoil/transitional_SA_LM_model_ConfigFile.cfg

@@ -11,220 +11,141 @@
 
 % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
 %
-% Physical governing equations (EULER, NAVIER_STOKES,
-%                               WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
-%                               POISSON_EQUATION)
 SOLVER= RANS
 %
-% Specify turbulent model (NONE, SA, SA_NEG, SST)
 KIND_TURB_MODEL= SA
 KIND_TRANS_MODEL= LM
 FREESTREAM_TURBULENCEINTENSITY= 0.001
 %
-% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
 MATH_PROBLEM= DIRECT
 %
-% Restart solution (NO, YES)
 RESTART_SOL= NO
 %
 
 % -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
 %
-% Mach number (non-dimensional, based on the free-stream values)
 MACH_NUMBER= 0.06
 %
-% Angle of attack (degrees, only for compressible flows)
 AOA= 2
 %
-% Free-stream temperature (288.15 K by default)
 FREESTREAM_TEMPERATURE= 288.15
 %
-% Reynolds number (non-dimensional, based on the free-stream values)
 REYNOLDS_NUMBER= 200000.0
 %
-% Reynolds length (1 m by default)
 REYNOLDS_LENGTH= 1.0
 
 % ---------------------- 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 length for pitching, rolling, and yawing non-dimensional moment
 REF_LENGTH= 1.0
 %
-% Reference area for force coefficients (0 implies automatic calculation)
 REF_AREA= 0
 %
-% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
-%                              FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
 REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_MACH
 
 % -------------------- 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_SYM= ( Symmetry )
 %
-% 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 )
 
 % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
 %
-% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
 NUM_METHOD_GRAD= GREEN_GAUSS
-%NUM_METHOD_GRAD_RECON= LEAST_SQUARES
 %
-% Courant-Friedrichs-Lewy condition of the finest grid
-%CFL_NUMBER= 1000.0
 CFL_NUMBER= 1
 %
-% Max Delta time
 %MAX_DELTA_TIME= 1E10
 %
-% Adaptive CFL number (NO, YES)
 CFL_ADAPT= YES
 %
-% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
-%                                        CFL max value )
 CFL_ADAPT_PARAM= ( 0.1, 2.0, 40.0, 1e10, 0.001 )
 %
-% Number of total iterations
 ITER= 100000
 
 % ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
 %
-% Linear solver or smoother for implicit formulations (BCGSTAB, FGMRES, SMOOTHER)
 LINEAR_SOLVER= FGMRES
 %
-% Preconditioner of the Krylov linear solver (ILU, LU_SGS, LINELET, JACOBI)
 LINEAR_SOLVER_PREC= LU_SGS
 %
-% Minimum error of the linear solver for implicit formulations
 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= ROE
 USE_VECTORIZATION= NO
 %
-% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
 MUSCL_FLOW= YES
 %
-% Slope limiter (VENKATAKRISHNAN, MINMOD)
 SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
 %
-% 2nd and 4th order artificial dissipation coefficients
 JST_SENSOR_COEFF= ( 0.5, 0.02 )
 %
-% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
 TIME_DISCRE_FLOW= EULER_IMPLICIT
 
 % ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
 %
-% Coefficient for the limiter
 VENKAT_LIMITER_COEFF= 0.05
 %
-% Freeze the value of the limiter after a number of iterations
 LIMITER_ITER= 99999
 
 % -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
 %
-% Convective numerical method (SCALAR_UPWIND)
 CONV_NUM_METHOD_TURB= SCALAR_UPWIND
 %
-% Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations.
-%           Required for 2nd order upwind schemes (NO, YES)
 MUSCL_TURB= NO
 %
-% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,
-%                BARTH_JESPERSEN, VAN_ALBADA_EDGE)
 SLOPE_LIMITER_TURB= NONE
 %
-% Time discretization (EULER_IMPLICIT)
 TIME_DISCRE_TURB= EULER_IMPLICIT
 %
-% Reduction factor of the CFL coefficient in the turbulence problem
 CFL_REDUCTION_TURB= 1.0
 
 % --------------------------- CONVERGENCE PARAMETERS --------------------------%
 %
 CONV_RESIDUAL_MINVAL= -13
 %
-% Min value of the residual (log10 of the residual)
 CONV_FIELD= ( RMS_DENSITY )
 %
-% Start convergence criteria at iteration number
 CONV_STARTITER= 500
 
 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
 %
-% Mesh input file
 MESH_FILENAME= ogrid_e387.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_FILENAME= restart_flow.dat
 %
-% Restart adjoint input file
-SOLUTION_ADJ_FILENAME= solution_adj.dat
+SOLUTION_FILENAME= restart_flow.dat
 %
-% Output file format (PARAVIEW, TECPLOT, STL)
-%TABULAR_FORMAT= CSV
-OUTPUT_FILES= (RESTART)
+OUTPUT_FILES= (RESTART, PARAVIEW, SURFACE_PARAVIEW)
 WRT_FORCES_BREAKDOWN= YES
 VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, RESIDUAL)
 HISTORY_OUTPUT= (ITER, LINSOL, RMS_RES, MAX_RES, AERO_COEFF, CFL_NUMBER)
 %
-% Output file convergence history (w/o extension)
 CONV_FILENAME= historySecond
 %
-% Output file restart flow
 RESTART_FILENAME= restart_flow.dat
 %
-% Output file restart adjoint
-RESTART_ADJ_FILENAME= restart_adj.dat
-%
-% Output file flow (w/o extension) variables
 VOLUME_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_FILENAME= surface_flow
 %
-% Output file surface adjoint coefficient (w/o extension)
-SURFACE_ADJ_FILENAME= surface_adjoint
-%
-% Writing solution file frequency
 OUTPUT_WRT_FREQ= 500
 %
-% Writing convergence history frequency
 SCREEN_WRT_FREQ_INNER= 10
 %
-% Screen output fields
 SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_DENSITY, RMS_INTERMITTENCY, RMS_RE_THETA_T, LIFT, DRAG, LINSOL_ITER_TRANS, LINSOL_RESIDUAL_TRANS, MAX_DENSITY, MAX_INTERMITTENCY, MAX_RE_THETA_T)
-
+%
 WRT_PERFORMANCE = YES