Adding UQ Tutorial

UQ_NACA0012/turb_NACA0012_uq.cfg

@@ -0,0 +1,251 @@
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+%                                                                              %
+% SU2 configuration file                                                       %
+% Case description: 2D NACA 0012 Airfoil Validation Case (compressible)        %
+%                   http://turbmodels.larc.nasa.gov/naca0012_val_sa.html       %
+% Author: Thomas D. Economon                                                   %
+% Institution: Stanford University                                             %
+% Date: Feb 18th, 2013                                                         %
+% File Version 3.2.1 "eagle"                                                   %
+%                                                                              %
+%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
+%
+% Physical governing equations (EULER, NAVIER_STOKES,
+%                               WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
+%                               POISSON_EQUATION)                             
+PHYSICAL_PROBLEM= NAVIER_STOKES
+%
+% 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
+%
+
+% -------------------- 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= 15.0
+%
+% 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
+%
+% Courant-Friedrichs-Lewy condition of the finest grid
+CFL_NUMBER= 10.0
+%
+% 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= ( 1.5, 0.5, 10.0, 100.0 )
+%
+% Number of total iterations
+EXT_ITER= 99999
+% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
+%
+% Coefficient for the limiter
+VENKAT_LIMITER_COEFF= 0.03
+%
+% Freeze the value of the limiter after a number of iterations
+LIMITER_ITER= 99999
+
+% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
+%
+% Linear solver or smoother for implicit formulations (BCGSTAB, MULTIGRID, FGMRES, SMOOTHER_JACOBI, 
+%                                                      SMOOTHER_ILU, SMOOTHER_LUSGS, 
+%                                                      SMOOTHER_LINELET)
+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-10
+%
+% 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= 0
+%
+% Multigrid pre-smoothing level
+MG_PRE_SMOOTH= ( 1, 1, 1, 1, 1, 1 )
+%
+% Multigrid post-smoothing level
+MG_POST_SMOOTH= ( 0, 0, 0, 0, 0, 0 )
+%
+% Jacobi implicit smoothing of the correction
+MG_CORRECTION_SMOOTH= ( 0, 0, 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= ROE
+%
+% 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
+
+% -------------------- 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= VENKATAKRISHNAN
+%
+% 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 --------------------------%
+%
+% Convergence criteria (CAUCHY, RESIDUAL)
+%
+CONV_CRITERIA= CAUCHY
+%
+% Residual reduction (order of magnitude with respect to the initial value)
+RESIDUAL_REDUCTION= 5
+%
+% Min value of the residual (log10 of the residual)
+RESIDUAL_MINVAL= -9
+%
+% Start convergence criteria at iteration number
+STARTCONV_ITER= 10
+%
+% Number of elements to apply the criteria
+CAUCHY_ELEMS= 100
+%
+% Epsilon to control the series convergence
+CAUCHY_EPS= 1E-5
+%
+% Function to apply the criteria (LIFT, DRAG, NEARFIELD_PRESS, SENS_GEOMETRY, 
+% 	      	    		 SENS_MACH, DELTA_LIFT, DELTA_DRAG)
+CAUCHY_FUNC_FLOW= DRAG
+
+% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
+%
+% Mesh input file
+MESH_FILENAME= n0012_225-65.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_FLOW_FILENAME= solution_flow_sst.dat
+%
+% Restart adjoint input file
+SOLUTION_ADJ_FILENAME= solution_adj.dat
+%
+% Output file format (PARAVIEW, TECPLOT, STL)
+OUTPUT_FORMAT= TECPLOT
+%
+% Output file convergence history (w/o extension) 
+CONV_FILENAME= history
+%
+% Output file restart flow
+RESTART_FLOW_FILENAME= restart_flow.dat
+%
+% Output file restart adjoint
+RESTART_ADJ_FILENAME= restart_adj.dat
+%
+% Output file flow (w/o extension) variables
+VOLUME_FLOW_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_FLOW_FILENAME= surface_flow
+%
+% Output file surface adjoint coefficient (w/o extension)
+SURFACE_ADJ_FILENAME= surface_adjoint
+%
+% Writing solution file frequency
+WRT_SOL_FREQ= 10000
+%
+% Writing convergence history frequency
+WRT_CON_FREQ= 1