remove descriptions of options in turb_NACA0012_sst_expliciteuler.cfg

Author: maxaehle

TestCases/rans/naca0012/turb_NACA0012_sst_expliciteuler.cfg

@@ -10,173 +10,71 @@
 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 
 % ------------- 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= SST
-%
-% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
 MATH_PROBLEM= DIRECT
-%
-% Restart solution (NO, YES)
 RESTART_SOL= NO
-%
-% Read binary restart files (YES, NO)
 READ_BINARY_RESTART= NO
-%
 
 % -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
-%
-% Mach number (non-dimensional, based on the free-stream values)
 MACH_NUMBER= 0.15
-%
-% Angle of attack (degrees, only for compressible flows)
 AOA= 10.0
-%
-% Free-stream temperature (288.15 K by default)
 FREESTREAM_TEMPERATURE= 300.0
-%
-% Reynolds number (non-dimensional, based on the free-stream values)
 REYNOLDS_NUMBER= 6.0E6
-%
-% 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= 1.0
-%
-% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
-%                              FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
 REF_DIMENSIONALIZATION= FREESTREAM_PRESS_EQ_ONE
 
 % -------------------- 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 )
 
 % ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
-%
-% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
 NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
 NUM_METHOD_GRAD_RECON= LEAST_SQUARES
-%
-% Courant-Friedrichs-Lewy condition of the finest grid
 CFL_NUMBER= 0.1
-%
-% Max Delta time
 MAX_DELTA_TIME= 1E10
-%
-% Number of total iterations
 ITER= 99999
 
 % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
-%
-% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
-%                              TURKEL_PREC, MSW)
 CONV_NUM_METHOD_FLOW= ROE
 USE_VECTORIZATION= YES
-%
-% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
 MUSCL_FLOW= YES
-%
-% Slope limiter (VENKATAKRISHNAN, MINMOD)
 SLOPE_LIMITER_FLOW= NONE
-%
-% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
 TIME_DISCRE_FLOW= EULER_EXPLICIT
 
 % -------------------- 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 (VENKATAKRISHNAN, MINMOD)
 SLOPE_LIMITER_TURB= NONE
-%
-% Time discretization (EULER_IMPLICIT)
 TIME_DISCRE_TURB= EULER_EXPLICIT
-%
-% Reduction factor of the CFL coefficient in the turbulence problem
 CFL_REDUCTION_TURB= 1.0
 
 % --------------------------- CONVERGENCE PARAMETERS --------------------------%
-%
-% Convergence field
 CONV_FIELD= RMS_DENSITY
-%
-% Min value of the residual (log10 of the residual)
 CONV_RESIDUAL_MINVAL= -12
-%
-% Start convergence criteria at iteration number
 CONV_STARTITER= 10
-%
-% Number of elements to apply the criteria
 CONV_CAUCHY_ELEMS= 100
-%
-% Epsilon to control the series convergence
 CONV_CAUCHY_EPS= 1E-6
-%
 
 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
-%
-% Mesh input file
 MESH_FILENAME= n0012_113-33.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= solution_flow_sst_fixedvalues.dat
-%
-% Output file format (PARAVIEW, TECPLOT, STL)
 TABULAR_FORMAT= CSV
-%
-% Output file convergence history (w/o extension) 
 CONV_FILENAME= history
-%
-% Output file restart flow
 RESTART_FILENAME= restart_flow.dat
-%
-% Output file flow (w/o extension) variables
 VOLUME_FILENAME= flow
-%
-% Output file surface flow coefficient (w/o extension)
 SURFACE_FILENAME= surface_flow
-%
-% Writing solution file frequency
 OUTPUT_WRT_FREQ= 10000
-%
-%
-% Screen output fields
 SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_TKE, RMS_DISSIPATION, LIFT, DRAG, LINSOL_RESIDUAL)
 OUTPUT_FILES= (RESTART_ASCII, PARAVIEW, SURFACE_PARAVIEW)