diff --git a/TestCases/engine/marker_engine_inflow/inv_channel_engine_inflow.cfg b/TestCases/engine/marker_engine_inflow/inv_channel_engine_inflow.cfg deleted file mode 100644 index d0bb330728d..00000000000 --- a/TestCases/engine/marker_engine_inflow/inv_channel_engine_inflow.cfg +++ /dev/null @@ -1,222 +0,0 @@ -%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% -% % -% SU2 configuration file % -% Case description: Inviscid, internal flow over a bump in a channel with % -% prescribed Mach number for outlet BC % -% Author: Thomas D. Economon , Berke C. Deveci % -% Institution: Stanford University % -% Date: 2024.05.28 % -% File Version 8.0.1 "Harrier" % -% % -%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% - -% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% -% -% Physical governing equations (EULER, NAVIER_STOKES, NS_PLASMA) -% -SOLVER= EULER -% -% 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= 0.1 -% -% Angle of attack (degrees, only for compressible flows) -AOA= 0.0 -% -% Side-slip angle (degrees, only for compressible flows) -SIDESLIP_ANGLE= 0.0 -% -% Free-stream pressure (101325.0 N/m^2 by default) -FREESTREAM_PRESSURE= 101300.0 -% -% Free-stream temperature (288.15 K by default) -FREESTREAM_TEMPERATURE= 288.0 - -% ---------------------- 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 - -% -------------------- BOUNDARY CONDITION DEFINITION --------------------------% -% -% Euler wall boundary marker(s) (NONE = no marker) -MARKER_EULER= ( upper_wall, lower_wall ) -% -% Inlet boundary type (TOTAL_CONDITIONS, MASS_FLOW) -INLET_TYPE= TOTAL_CONDITIONS -% -% Inlet boundary marker(s) (NONE = no marker) -% Format: ( inlet marker, total temperature, total pressure, flow_direction_x, -% flow_direction_y, flow_direction_z, ... ) where flow_direction is -% a unit vector. -% Default: Mach ~ 0.1 -MARKER_INLET= ( inlet, 288.6, 102010.0, 1.0, 0.0, 0.0 ) -% Comment above line and uncomment next for Mach ~ 0.7 (transonic) -%MARKER_INLET= ( inlet, 316.224, 140513.23, 1.0, 0.0, 0.0 ) -% -% Engine inflow boundary marker(s) (NONE = no marker) -% Format: (engine inflow marker, fan face Mach, ... ) -MARKER_ENGINE_INFLOW= ( outlet, 0.1) -ENGINE_INFLOW_TYPE= FAN_FACE_MACH -% Damping factor for the engine inflow. -DAMP_ENGINE_INFLOW= 0.2 -% Evaluation frequency for engine marker values -BC_EVAL_FREQ = 1 - -% ------------------------ SURFACES IDENTIFICATION ----------------------------% -% -% Marker(s) of the surface to be plotted or designed -MARKER_PLOTTING= ( lower_wall ) -% -% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated -MARKER_MONITORING= ( upper_wall, lower_wall ) - -% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% -% -% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES) -NUM_METHOD_GRAD= GREEN_GAUSS -% -% Courant-Friedrichs-Lewy condition of the finest grid -CFL_NUMBER= 50.0 -% -% 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, 50.0, 1e10 ) -% -% Runge-Kutta alpha coefficients -RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) -% -% Number of total iterations -ITER= 999999 - -% ------------------------ LINEAR SOLVER DEFINITION ---------------------------% -% -% Linear solver for implicit formulations (BCGSTAB, FGMRES) -LINEAR_SOLVER= FGMRES -% -% Preconditioner of the Krylov linear solver (ILU, JACOBI, LINELET, LU_SGS) -LINEAR_SOLVER_PREC= ILU -% -% 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= 20 - -% -------------------------- 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= 1.0 -% -% Damping factor for the correction prolongation -MG_DAMP_PROLONGATION= 1.0 - -% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% -% -% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC, -% TURKEL_PREC, MSW) -CONV_NUM_METHOD_FLOW= JST -% -% 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 - -% --------------------------- CONVERGENCE PARAMETERS --------------------------% -% -% Convergence criteria (CAUCHY, RESIDUAL) -CONV_FIELD= RMS_DENSITY -% -% Min value of the residual (log10 of the residual) -CONV_RESIDUAL_MINVAL= -10 -% -% 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-10 - -% ------------------------- INPUT/OUTPUT INFORMATION --------------------------% -% -% Mesh input file -MESH_FILENAME= ../../euler/channel/mesh_channel_256x128.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.dat -% -% Restart adjoint input file -SOLUTION_ADJ_FILENAME= solution_adj.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 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 -% -% -% Screen output -SCREEN_OUTPUT= (INNER_ITER, WALL_TIME, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG)