From cced02e4f10000b837abe4a1589e8db9989d9495 Mon Sep 17 00:00:00 2001 From: "Thomas D. Economon" Date: Tue, 1 Sep 2015 02:17:09 -0700 Subject: [PATCH] Updated version numbers to 4.0.1. [ci skip] --- README.md | 2 +- .../rotating_naca0012/rotating_NACA0012.cfg | 344 ------------------ 2 files changed, 1 insertion(+), 345 deletions(-) delete mode 100644 optimization_euler/rotating_naca0012/rotating_NACA0012.cfg diff --git a/README.md b/README.md index 4ad71176..655969ff 100644 --- a/README.md +++ b/README.md @@ -1,5 +1,5 @@ ----------------------------------------------------------- - SU2 (ver. 4.0.0 "Cardinal"): The Open-Source CFD Code + SU2 (ver. 4.0.1 "Cardinal"): The Open-Source CFD Code ----------------------------------------------------------- Computational analysis tools have revolutionized the way we design aerospace systems, but most established codes are proprietary, unavailable, or prohibitively expensive for many users. The SU2 team is changing this, making computational analysis and design freely available as open-source software and involving everyone in its creation and development. diff --git a/optimization_euler/rotating_naca0012/rotating_NACA0012.cfg b/optimization_euler/rotating_naca0012/rotating_NACA0012.cfg deleted file mode 100644 index 1469821a..00000000 --- a/optimization_euler/rotating_naca0012/rotating_NACA0012.cfg +++ /dev/null @@ -1,344 +0,0 @@ -%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% -% % -% SU2 configuration file % -% Case description: Rotating NACA0012 airfoil in transonic, inviscid flow % -% Author: Thomas D. Economon % -% Institution: Stanford University % -% Date: 2013.03.06 % -% File Version 4.0.0 "Cardinal" % -% % -%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% - -% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% -% -% Physical governing equations (EULER, NAVIER_STOKES, -% TNE2_EULER, TNE2_NAVIER_STOKES, -% WAVE_EQUATION, HEAT_EQUATION, LINEAR_ELASTICITY, -% POISSON_EQUATION) -PHYSICAL_PROBLEM= EULER -% -% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT) -MATH_PROBLEM= DIRECT -% -% Restart solution (NO, YES) -RESTART_SOL= NO - -% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------% -% -% Mach number (non-dimensional, based on the free-stream values) -MACH_NUMBER= 0.0 -% -% Angle of attack (degrees) -AoA= 0.0 -% -% Side-slip angle (degrees) -SIDESLIP_ANGLE= 0.0 -% -% Free-stream pressure (101325.0 N/m^2 by default, only Euler flows) -FREESTREAM_PRESSURE= 101325.0 -% -% Free-stream temperature (288.15 K by default) -FREESTREAM_TEMPERATURE= 288.15 - -% ---------------------- 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_MOMENT= 1.0 -% -% Reference area for force coefficients (0 implies automatic calculation) -REF_AREA= 1.0 - -% ----------------------- DYNAMIC MESH DEFINITION -----------------------------% -% -% Dynamic mesh simulation (NO, YES) -GRID_MOVEMENT= YES -% -% Type of dynamic mesh (NONE, RIGID_MOTION, DEFORMING, ROTATING_FRAME, -% MOVING_WALL, FLUID_STRUCTURE, AEROELASTIC, EXTERNAL) -GRID_MOVEMENT_KIND= ROTATING_FRAME -% -% Motion mach number (non-dimensional). Used for intitializing a viscous flow -% with the Reynolds number and for computing force coeffs. with dynamic meshes. -MACH_MOTION= 0.79578199852934983 -% -% Coordinates of the motion origin -MOTION_ORIGIN_X= 0.5 -MOTION_ORIGIN_Y= -32.0 -MOTION_ORIGIN_Z= 0.0 -% -% Angular velocity vector (rad/s) about the motion origin -ROTATION_RATE_X = 0.0 -ROTATION_RATE_Y = 0.0 -ROTATION_RATE_Z = 8.25 - -% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------% -% -% Marker of the Euler boundary (0 = no marker) -MARKER_EULER= ( airfoil ) -% -% Marker of the far field (0 = no marker) -MARKER_FAR= ( farfield ) -% -% Marker of the surface which is going to be plotted or designed -MARKER_PLOTTING= ( airfoil ) -% -% Marker of the surface where the functional (Cd, Cl, etc.) will be evaluated -MARKER_MONITORING= ( airfoil ) - -% ------------- COMMON PARAMETERS TO DEFINE 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= 6.0 -% -% Adaptive CFL number (NO, YES) -CFL_ADAPT= NO -% -% Parameters of the adaptive CFL number (factor down, factor up, CFL min value, -% CFL max value ) -CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 ) -% -% Runge-Kutta alpha coefficients -RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) -% -% Number of total iterations -EXT_ITER= 99999 - -% ------------------------ LINEAR SOLVER DEFINITION ---------------------------% -% -% Linear solver for implicit formulations (BCGSTAB, FGMRES) -LINEAR_SOLVER= FGMRES -% -% Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS) -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 - -% -------------------------- 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 PreSmoothing Level -MG_PRE_SMOOTH= ( 1, 2, 3, 3 ) -% -% Multi-Grid PostSmoothing 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= 0.95 -% -% Damping factor for the correction prolongation -MG_DAMP_PROLONGATION= 0.95 - -% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% -% -% Convective numerical method (JST, LAX-FRIEDRICH, ROE, AUSM, HLLC) -CONV_NUM_METHOD_FLOW= JST -% -% Slope limiter (VENKATAKRISHNAN) -SLOPE_LIMITER_FLOW= VENKATAKRISHNAN -% -% Coefficient for the limiter -LIMITER_COEFF= 0.3 -% -% 1st, 2nd and 4th order artificial dissipation coefficients -AD_COEFF_FLOW= ( 0.15, 0.5, 0.02 ) -% -% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) -TIME_DISCRE_FLOW= EULER_IMPLICIT - -% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------% -% -% Adjoint problem boundary condition (DRAG, LIFT, SIDEFORCE, MOMENT_X, -% MOMENT_Y, MOMENT_Z, EFFICIENCY, -% EQUIVALENT_AREA, NEARFIELD_PRESSURE, -% FORCE_X, FORCE_Y, FORCE_Z, THRUST, -% TORQUE, FREE_SURFACE) -OBJECTIVE_FUNCTION= DRAG -% -% Convective numerical method (JST, LAX-FRIEDRICH, ROE) -CONV_NUM_METHOD_ADJFLOW= JST -% -% Slope limiter (VENKATAKRISHNAN, SHARP_EDGES) -SLOPE_LIMITER_ADJFLOW= SHARP_EDGES -% -% Coefficient for the sharp edges limiter -SHARP_EDGES_COEFF= 3.0 -% -% 1st, 2nd, and 4th order artificial dissipation coefficients -AD_COEFF_ADJFLOW= ( 0.15, 0.0, 0.02 ) -% -% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT) -TIME_DISCRE_ADJFLOW= EULER_IMPLICIT -% -% Reduction factor of the CFL coefficient in the adjoint problem -CFL_REDUCTION_ADJFLOW= 0.8 -% -% Limit value for the adjoint variable -LIMIT_ADJFLOW= 1E6 -% -% Remove sharp edges from the sensitivity evaluation (NO, YES) -SENS_REMOVE_SHARP= NO -% -% Sensitivity smoothing (NONE, SOBOLEV, BIGRID) -SENS_SMOOTHING= NONE -% -% Adjoint frozen viscosity (NO, YES) -FROZEN_VISC= YES - -% ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------% -% -% Geometrical evaluation mode (FUNCTION, GRADIENT) -GEO_MODE= FUNCTION -% -% Marker(s) of the surface where geometrical based func. will be evaluated -GEO_MARKER= ( airfoil ) - -% ------------------------ GRID DEFORMATION PARAMETERS ------------------------% -% Kind of deformation (FFD_SETTING, HICKS_HENNE, HICKS_HENNE_NORMAL, PARABOLIC, -% HICKS_HENNE_SHOCK, NACA_4DIGITS, DISPLACEMENT, ROTATION, -% FFD_CONTROL_POINT, FFD_DIHEDRAL_ANGLE, FFD_TWIST_ANGLE, -% FFD_ROTATION) -DV_KIND= HICKS_HENNE -% -% Marker of the surface in which we are going apply the shape deformation -DV_MARKER= ( airfoil ) -% -% Parameters of the shape deformation -% - HICKS_HENNE_FAMILY ( Lower(0)/Upper(1) side, x_Loc ) -% - NACA_4DIGITS ( 1st digit, 2nd digit, 3rd and 4th digit ) -% - PARABOLIC ( 1st digit, 2nd and 3rd digit ) -% - DISPLACEMENT ( x_Disp, y_Disp, z_Disp ) -% - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) -DV_PARAM= ( 1, 0.5 ) -% -% Old value of the deformation for incremental deformations -DV_VALUE= 0.05 -% -% Visualize the deformation (NO, YES) -VISUALIZE_DEFORMATION= NO - -% --------------------------- CONVERGENCE PARAMETERS --------------------------% -% Convergence criteria (CAUCHY, RESIDUAL) -% -CONV_CRITERIA= RESIDUAL -% -% Residual reduction (order of magnitude with respect to the initial value) -RESIDUAL_REDUCTION= 8 -% -% Min value of the residual (log10 of the residual) -RESIDUAL_MINVAL= -13 -% -% Start Cauchy 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-6 -% -% Function to apply the criteria (LIFT, DRAG, SENS_GEOMETRY, SENS_MACH, -% DELTA_LIFT, DELTA_DRAG) -CAUCHY_FUNC_FLOW= DRAG -CAUCHY_FUNC_ADJFLOW= SENS_MACH - -% ------------------------- INPUT/OUTPUT INFORMATION --------------------------% -% -% Mesh input file -MESH_FILENAME= mesh_NACA0012_rot.su2 -% -% Mesh input file format (SU2, CGNS, NETCDF_ASCII) -MESH_FORMAT= SU2 -% -MESH_OUT_FILENAME= mesh_out.su2 -% -% Restart flow input file -SOLUTION_FLOW_FILENAME= solution_flow.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 linear flow -RESTART_LIN_FILENAME= restart_lin.dat -% -% Output file flow (w/o extension) variables -VOLUME_FLOW_FILENAME= flow -% -% Output file adjoint (w/o extension) variables -VOLUME_ADJ_FILENAME= adjoint -% -% Output file linearized (w/o extension) variables -VOLUME_LIN_FILENAME= linearized -% -% 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 -% -% Output file surface linear coefficient (w/o extension) -SURFACE_LIN_FILENAME= surface_linear -% -% Writing solution file frequency -WRT_SOL_FREQ= 250 -% -% Writing convergence history frequency -WRT_CON_FREQ= 1 - -% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------% -% Available Objective functions -% DRAG, LIFT, SIDEFORCE, PRESSURE, FORCE_X, FORCE_Y, -% FORCE_Z, MOMENT_X, MOMENT_Y, MOMENT_Z, EFFICIENCY, -% EQUIVALENT_AREA, THRUST, TORQUE, FREE_SURFACE - -% Optimization objective function with optional scaling factor -% ex= Objective * Scale -OPT_OBJECTIVE= DRAG * 0.001 - -% Optimization constraint functions with scaling factors, separated by semicolons -% ex= (Objective = Value ) * Scale, use '>','<','=' -OPT_CONSTRAINT= ( MAX_THICKNESS > 0.12 ) * 0.001 -% -% List of design variables (Design variables are separated by semicolons) -% From 1 to 99, Geometrycal design variables. -% - HICKS_HENNE ( 1, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc ) -% - NACA_4DIGITS ( 4, Scale | Mark. List | 1st digit, 2nd digit, 3rd and 4th digit ) -% - ROTATION ( 6, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn ) -% From 100 to 199, Flow solver design variables. -% - MACH_NUMBER ( 101, Scale | Markers List ) -% - AOA ( 102, Scale | Markers List ) -DEFINITION_DV= ( 1, 1.0 | airfoil | 0, 0.961538461538 ); ( 1, 1.0 | airfoil | 0, 0.923076923077 ); ( 1, 1.0 | airfoil | 0, 0.884615384615 ); ( 1, 1.0 | airfoil | 0, 0.846153846154 ); ( 1, 1.0 | airfoil | 0, 0.807692307692 ); ( 1, 1.0 | airfoil | 0, 0.769230769231 ); ( 1, 1.0 | airfoil | 0, 0.730769230769 ); ( 1, 1.0 | airfoil | 0, 0.692307692308 ); ( 1, 1.0 | airfoil | 0, 0.653846153846 ); ( 1, 1.0 | airfoil | 0, 0.615384615385 ); ( 1, 1.0 | airfoil | 0, 0.576923076923 ); ( 1, 1.0 | airfoil | 0, 0.538461538462 ); ( 1, 1.0 | airfoil | 0, 0.5 ); ( 1, 1.0 | airfoil | 0, 0.461538461538 ); ( 1, 1.0 | airfoil | 0, 0.423076923077 ); ( 1, 1.0 | airfoil | 0, 0.384615384615 ); ( 1, 1.0 | airfoil | 0, 0.346153846154 ); ( 1, 1.0 | airfoil | 0, 0.307692307692 ); ( 1, 1.0 | airfoil | 0, 0.269230769231 ); ( 1, 1.0 | airfoil | 0, 0.230769230769 ); ( 1, 1.0 | airfoil | 0, 0.192307692308 ); ( 1, 1.0 | airfoil | 0, 0.153846153846 ); ( 1, 1.0 | airfoil | 0, 0.115384615385 ); ( 1, 1.0 | airfoil | 0, 0.0769230769231 ); ( 1, 1.0 | airfoil | 0, 0.0384615384615 ); ( 1, 1.0 | airfoil | 1, 0.0384615384615 ); ( 1, 1.0 | airfoil | 1, 0.0769230769231 ); ( 1, 1.0 | airfoil | 1, 0.115384615385 ); ( 1, 1.0 | airfoil | 1, 0.153846153846 ); ( 1, 1.0 | airfoil | 1, 0.192307692308 ); ( 1, 1.0 | airfoil | 1, 0.230769230769 ); ( 1, 1.0 | airfoil | 1, 0.269230769231 ); ( 1, 1.0 | airfoil | 1, 0.307692307692 ); ( 1, 1.0 | airfoil | 1, 0.346153846154 ); ( 1, 1.0 | airfoil | 1, 0.384615384615 ); ( 1, 1.0 | airfoil | 1, 0.423076923077 ); ( 1, 1.0 | airfoil | 1, 0.461538461538 ); ( 1, 1.0 | airfoil | 1, 0.5 ); ( 1, 1.0 | airfoil | 1, 0.538461538462 ); ( 1, 1.0 | airfoil | 1, 0.576923076923 ); ( 1, 1.0 | airfoil | 1, 0.615384615385 ); ( 1, 1.0 | airfoil | 1, 0.653846153846 ); ( 1, 1.0 | airfoil | 1, 0.692307692308 ); ( 1, 1.0 | airfoil | 1, 0.730769230769 ); ( 1, 1.0 | airfoil | 1, 0.769230769231 ); ( 1, 1.0 | airfoil | 1, 0.807692307692 ); ( 1, 1.0 | airfoil | 1, 0.846153846154 ); ( 1, 1.0 | airfoil | 1, 0.884615384615 ); ( 1, 1.0 | airfoil | 1, 0.923076923077 ); ( 1, 1.0 | airfoil | 1, 0.961538461538 )