Merge pull request #1845 from su2code/test_case_clean_up

Cleaning up test cases suite

Author: WallyMaier

TestCases/aeroelastic/aeroelastic_NACA64A010.cfg

@@ -11,82 +11,43 @@
 
 % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
 %
-% Physical governing equations (EULER, NAVIER_STOKES,
-%                               WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
-%                               POISSON_EQUATION)
 SOLVER= EULER
-%
-% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
 MATH_PROBLEM= DIRECT
-%
-% 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= 0.85
-%
-% Angle of attack (degrees, only for compressible flows)
 AOA= 1.0
-%
-% Free-stream pressure (101325.0 N/m^2, 2116.216 psf by default)
 FREESTREAM_PRESSURE= 101325.0
-%
-% Free-stream temperature (288.15 K, 518.67 R by default)
 FREESTREAM_TEMPERATURE= 288.15
 
 % ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
 %
-% Reference origin for moment computation (m or in)
 REF_ORIGIN_MOMENT_X = -0.5
 REF_ORIGIN_MOMENT_Y = 0.00
 REF_ORIGIN_MOMENT_Z = 0.00
-%
-% Reference length for pitching, rolling, and yawing non-dimensional
-% moment (m or in)
 REF_LENGTH= 1.0
-%
-% Reference area for force coefficients (0 implies automatic
-% calculation) (m^2 or in^2)
 REF_AREA= 1.0
-%
-% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
-%                              FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
 REF_DIMENSIONALIZATION= DIMENSIONAL
 
 % ------------------------- UNSTEADY SIMULATION -------------------------------%
 %
-% Time domain
 TIME_DOMAIN=YES
-%
-% Unsteady simulation (NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER, 
-%                      DUAL_TIME_STEPPING-2ND_ORDER, SPECTRAL_METHOD)
 TIME_MARCHING= DUAL_TIME_STEPPING-2ND_ORDER
-%
-% Time Step for dual time stepping simulations (s)
 TIME_STEP= 0.00174532925199
 % 36 steps per period, based on the pitch natural frequency
 %
-% Total Physical Time for dual time stepping simulations (s)
 MAX_TIME= 50.0
-%
-% Number of internal iterations (dual time method)
 INNER_ITER= 100
 
 % ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
-SURFACE_MOVEMENT= AEROELASTIC
 %
-% Motion mach number (non-dimensional). Used for initializing a viscous flow
-% with the Reynolds number and for computing force coeffs. with dynamic meshes.
+SURFACE_MOVEMENT= AEROELASTIC
 MACH_MOTION= 0.85
-%
-% Moving wall boundary marker(s) (NONE = no marker, ignored for RIGID_MOTION)
 MARKER_MOVING= ( airfoil )
 
 % -------------- AEROELASTIC SIMULATION (Typical Section Model) ---------------%
-% Activated by GRID_MOVEMENT_KIND option
 %
 % The flutter speed index (modifies the freestream condition in the solver)
 FLUTTER_SPEED_INDEX = 1.3
@@ -113,188 +74,88 @@ AEROELASTIC_ITER = 3
 
 % --------------------------- GUST SIMULATION ---------------------------------%
 %
-% Apply a wind gust (NO, YES)
 WIND_GUST = NO
-%
-% Type of gust (NONE, TOP_HAT, SINE, ONE_M_COSINE, VORTEX, EOG)
 GUST_TYPE = TOP_HAT
-%
-% Direction of the gust (X_DIR or Y_DIR)
 GUST_DIR = Y_DIR
-%
-% Gust wavelenght (meters)
 GUST_WAVELENGTH= 7.90876841815
 % 1/4 of period based on the pitch natural frequency
 %
-% Number of gust periods
 GUST_PERIODS= 1.0
-%
-% Gust amplitude (m/s)
 GUST_AMPL= 8.78841285061
 % Corresponds to 1 deg AoA.
 %
-% Time at which to begin the gust (sec)
 GUST_BEGIN_TIME= 0.0
-%
-% Location at which the gust begins (meters) */
 GUST_BEGIN_LOC= -7.90876841815
 
 % -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
 %
-% Euler wall boundary marker(s) (NONE = no marker)
 MARKER_EULER= ( airfoil )
-%
-% Far-field boundary marker(s) (NONE = no marker)
 MARKER_FAR= ( farfield )
 
 % ------------------------ SURFACES IDENTIFICATION ----------------------------%
 %
-% Marker(s) of the surface in the surface flow solution file
 MARKER_PLOTTING = ( airfoil )
-%
-% Marker(s) of the surface where the non-dimensional coefficients are 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
-%
-% CFL number (stating value for the adaptive CFL number)
 CFL_NUMBER= 4.0
 
 % ------------------------ 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-4
-%
-% Max number of iterations of the linear solver for the implicit formulation
 LINEAR_SOLVER_ITER= 2
 
 % -------------------------- MULTIGRID PARAMETERS -----------------------------%
 %
-% Multi-grid levels (0 = no multi-grid)
 MGLEVEL= 3
-%
-% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
 MGCYCLE= W_CYCLE
-%
-% Multi-grid pre-smoothing level
 MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
-%
-% 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= 0.75
-%
-% Damping factor for the correction prolongation
 MG_DAMP_PROLONGATION= 0.75
 
 % -------------------- 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)
 MUSCL_FLOW= YES
-%
-% Slope limiter (VENKATAKRISHNAN, BARTH_JESPERSEN)
 SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
-%
-% Entropy fix coefficient (0.0 implies no entropy fixing, 1.0 implies scalar
-%                          artificial dissipation)
 ENTROPY_FIX_COEFF= 0.001
-%
-% 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
 
 % ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
 %
-% Linear solver or smoother for implicit formulations (FGMRES, RESTARTED_FGMRES, BCGSTAB)
 DEFORM_LINEAR_SOLVER= FGMRES
-%
-% Preconditioner of the Krylov linear solver (ILU, LU_SGS, JACOBI)
 DEFORM_LINEAR_SOLVER_PREC= LU_SGS
-%
-% Number of smoothing iterations for mesh deformation
 DEFORM_LINEAR_SOLVER_ITER= 500
-%
-% Number of nonlinear deformation iterations (surface deformation increments)
 DEFORM_NONLINEAR_ITER= 1
-%
-% Print the residuals during mesh deformation to the console (YES, NO)
 DEFORM_CONSOLE_OUTPUT= NO
-%
-% Minimum residual criteria for the linear solver convergence of grid deformation
 DEFORM_LINEAR_SOLVER_ERROR= 1E-14
-%
-% Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME, 
-%                                          WALL_DISTANCE, CONSTANT_STIFFNESS)
 DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME
 
 % --------------------------- CONVERGENCE PARAMETERS --------------------------%
 %
-% Number of total iterations
 TIME_ITER= 360
-%
-% Min value of the residual (log10 of the residual)
 CONV_RESIDUAL_MINVAL= -8
-%
-% Start convergence criteria at iteration number
 CONV_STARTITER= 0
-%
-% Number of elements to apply the criteria
 CONV_CAUCHY_ELEMS= 100
-%
-% Epsilon to control the series convergence
 CONV_CAUCHY_EPS= 1E-10
-%
 
 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
 %
-% Mesh input file
 MESH_FILENAME= mesh_NACA64A010_hybrid_inv.su2
-%
-% Mesh input file format (SU2, CGNS)
 MESH_FORMAT= SU2
-%
-% Restart flow input file
 SOLUTION_FILENAME= solution_flow.dat
-%
 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 for physical time steps (dual time)
 OUTPUT_WRT_FREQ= 1000
-%
-%
-% Screen output
 SCREEN_OUTPUT= (TIME_ITER, INNER_ITER, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG_ON_SURFACE, PLUNGE, PITCH) 
-%
-OUTPUT_FILES= (RESTART_ASCII)
-
+OUTPUT_FILES= (RESTART_ASCII)

TestCases/axisymmetric_rans/air_nozzle/air_nozzle_restart.cfg

@@ -13,36 +13,32 @@
 SOLVER= RANS
 KIND_TURB_MODEL= SST
 RESTART_SOL= YES
-%
 AXISYMMETRIC= YES
-%
+
 % -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
 %
 MACH_NUMBER= 1E-9
-%
 INIT_OPTION= TD_CONDITIONS
-%
 FREESTREAM_OPTION= TEMPERATURE_FS
 FREESTREAM_PRESSURE= 1400000
 FREESTREAM_TEMPERATURE= 373.15
-%
 REF_DIMENSIONALIZATION= DIMENSIONAL
-%
+
 % ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
 %
 FLUID_MODEL= STANDARD_AIR
-%
+
 % --------------------------- VISCOSITY MODEL ---------------------------------%
 %
 VISCOSITY_MODEL= CONSTANT_VISCOSITY
 MU_CONSTANT= 1.716E-5
-%
+
 % --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
 %
 CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
 PRANDTL_LAM= 0.72
 PRANDTL_TURB= 0.90
-%
+
 % -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
 %
 MARKER_HEATFLUX= ( WALL, 0.0 )
@@ -58,46 +54,43 @@ CFL_NUMBER= 1000.0
 CFL_ADAPT= NO
 MAX_DELTA_TIME= 1E6
 OBJECTIVE_FUNCTION= DRAG
-%
+
 % ----------- SLOPE LIMITER AND DISSIPATION SENSOR DEFINITION -----------------%
 %
 MUSCL_FLOW= YES
 SLOPE_LIMITER_FLOW= NONE
-%
+
 % ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
 %
 LINEAR_SOLVER= FGMRES
 LINEAR_SOLVER_PREC= ILU
 LINEAR_SOLVER_ILU_FILL_IN= 0
 LINEAR_SOLVER_ERROR= 0.01
 LINEAR_SOLVER_ITER= 10
-%
+
 % -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
 %
 CONV_NUM_METHOD_FLOW= ROE
 ENTROPY_FIX_COEFF= 0.1
 TIME_DISCRE_FLOW= EULER_IMPLICIT
-%
+
 % -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
 %
 CONV_NUM_METHOD_TURB= SCALAR_UPWIND
 TIME_DISCRE_TURB= EULER_IMPLICIT
 CFL_REDUCTION_TURB= 1.0
-%
+
 % --------------------------- CONVERGENCE PARAMETERS --------------------------%
 %
 ITER= 3000
 CONV_RESIDUAL_MINVAL= -12
 CONV_STARTITER= 10
-%
+
 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
 %
 MESH_FILENAME= nozzle.su2
-%
 SOLUTION_FILENAME= solution_flow.dat
 RESTART_FILENAME= restart_flow.dat
 OUTPUT_WRT_FREQ= 1000
-%
-% Note: This cfg is used for a primal and adjoint Testcase, therefore both residuals are present here.
 SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_ENERGY, RMS_TKE, RMS_DISSIPATION, TOTAL_HEATFLUX, \
                 RMS_ADJ_DENSITY, RMS_ADJ_ENERGY, RMS_ADJ_TKE, RMS_ADJ_DISSIPATION, SENS_AOA, SENS_MACH)