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new onera optimization/tutorial 8 config file credit: Santiago
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| %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
| % % | ||
| % Stanford University unstructured (SU2) configuration file % | ||
| % Case description: Optimization case for the ONERA M6 wing in inviscid flow % | ||
| % Author: Francisco Palacios % | ||
| % Institution: Stanford University % | ||
| % Date: 09.27.2013 % | ||
| % File Version 2.0.7 % | ||
| % % | ||
| %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% | ||
|
|
||
| % ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% | ||
| % | ||
| % Physical governing equations (EULER, NAVIER_STOKES, | ||
| % PLASMA_EULER, PLASMA_NAVIER_STOKES, | ||
| % FLUID_STRUCTURE_EULER, FLUID_STRUCTURE_NAVIER_STOKES, | ||
| % AEROACOUSTIC_EULER, AEROACOUSTIC_NAVIER_STOKES, | ||
| % WAVE_EQUATION, HEAT_EQUATION, LINEAR_ELASTICITY) | ||
| PHYSICAL_PROBLEM= EULER | ||
| % | ||
| % Mathematical problem (DIRECT, ADJOINT) | ||
| MATH_PROBLEM= DIRECT | ||
| % | ||
| % Restart solution (NO, YES) | ||
| RESTART_SOL= YES | ||
|
|
||
| % -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% | ||
| % | ||
| % Mach number (non-dimensional, based on the free-stream values) | ||
| MACH_NUMBER= 0.8395 | ||
| % | ||
| % Angle of attack (degrees) | ||
| AoA= 3.06 | ||
| % | ||
| % Side-slip angle (degrees) | ||
| SIDESLIP_ANGLE= 0.0 | ||
| % | ||
| % Free-stream pressure (101325.0 N/m^2 by default, only for Euler equations) | ||
| FREESTREAM_PRESSURE= 101325.0 | ||
| % | ||
| % Free-stream temperature (273.15K by default) | ||
| FREESTREAM_TEMPERATURE= 273.15 | ||
|
|
||
| % --------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------% | ||
| % | ||
| % Ratio of specific heats (1.4 (air), only for compressible flows) | ||
| GAMMA_VALUE= 1.4 | ||
| % | ||
| % Specific gas constant (287.87 J/kg*K (air), only for compressible flows) | ||
| GAS_CONSTANT= 287.87 | ||
|
|
||
| % ---------------------- REFERENCE VALUE DEFINITION ---------------------------% | ||
| % | ||
| % Conversion factor for converting the grid to meters | ||
| CONVERT_TO_METER= 1.0 | ||
| % | ||
| % Reference origin for moment computation | ||
| REF_ORIGIN_MOMENT_X = 0.2015 | ||
| 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= 0.64607 | ||
| % | ||
| % Reference area for force coefficients (0 implies automatic calculation) | ||
| REF_AREA= 0 | ||
| % | ||
| % Reference pressure (101325.0 N/m^2 by default) | ||
| REF_PRESSURE= 101325.0 | ||
| % | ||
| % Reference temperature (273.15 K by default) | ||
| REF_TEMPERATURE= 273.15 | ||
| % | ||
| % Reference density (1.2886 Kg/m^3 (air), 998.2 Kg/m^3 (water)) | ||
| REF_DENSITY= 1.2886 | ||
| % | ||
| % Reference element length for computing the slope and sharp edges limiters. | ||
| REF_ELEM_LENGTH= 0.1 | ||
| % | ||
| % Reference coefficient (sensitivity) for detecting sharp edges. | ||
| REF_SHARP_EDGES= 3.0 | ||
|
|
||
| % ----------------------- BOUNDARY CONDITION DEFINITION -----------------------% | ||
| % | ||
| % Marker of the Euler boundary (0 implies no marker) | ||
| MARKER_EULER= ( UPPER_SIDE, LOWER_SIDE, TIP ) | ||
| % | ||
| % Marker of the far field (0 implies no marker) | ||
| MARKER_FAR= ( XNORMAL_FACES, ZNORMAL_FACES, YNORMAL_FACE ) | ||
| % | ||
| % Marker of symmetry boundary (0 implies no marker) | ||
| MARKER_SYM= ( SYMMETRY_FACE ) | ||
| % | ||
| % Marker of the surface which is going to be plotted or designed | ||
| MARKER_PLOTTING= ( UPPER_SIDE, LOWER_SIDE, TIP ) | ||
| % | ||
| % Marker of the surface where the functional (Cd, Cl, etc.) will be evaluated | ||
| MARKER_MONITORING= ( UPPER_SIDE, LOWER_SIDE, TIP ) | ||
|
|
||
| % ------------- 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 | ||
| % | ||
| % CFL ramp (factor, number of iterations, CFL limit) | ||
| CFL_RAMP= ( 1.0, 50, 1.0 ) | ||
| % | ||
| % Runge-Kutta alpha coefficients | ||
| RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 ) | ||
| % | ||
| % Number of total iterations | ||
| EXT_ITER= 2000 | ||
|
|
||
| % ------------------------ LINEAR SOLVER DEFINITION ---------------------------% | ||
| % | ||
| % Linear solver for the implicit formulation (BCGSTAB, FGMRES) | ||
| LINEAR_SOLVER= FGMRES | ||
| % | ||
| % Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS) | ||
| LINEAR_SOLVER_PREC= LU_SGS | ||
| % | ||
| % Min error of the linear solver for the implicit formulation | ||
| 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= 2 | ||
| % | ||
| % Multi-Grid Cycle (0 = V cycle, 1 = W Cycle) | ||
| MGCYCLE= 0 | ||
| % | ||
| % Reduction factor of the CFL coefficient in the coarse levels | ||
| MG_CFL_REDUCTION= 0.9 | ||
| % | ||
| % Maximum number of children in the agglomeration stage | ||
| MAX_CHILDREN= 250 | ||
| % | ||
| % Maximum length of an agglomerated element (compared with the domain) | ||
| MAX_DIMENSION= 0.15 | ||
| % | ||
| % 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= 0.9 | ||
| % | ||
| % Damping factor for the correction prolongation | ||
| MG_DAMP_PROLONGATION= 0.9 | ||
|
|
||
| % --------------------- FLOW NUMERICAL METHOD DEFINITION ----------------------% | ||
| % Convective numerical method: (JST, LAX-FRIEDRICH, ROE-1ST_ORDER, | ||
| % ROE-2ND_ORDER) | ||
| CONV_NUM_METHOD_FLOW= JST | ||
| % | ||
| % Slope limiter: (NONE, VENKATAKRISHNAN) | ||
| SLOPE_LIMITER_FLOW= NONE | ||
| % | ||
| % Coefficient for the limiter | ||
| LIMITER_COEFF= 0.3 | ||
| % | ||
| % 1st, 2nd and 4th order artificial dissipation coefficients | ||
| AD_COEFF_FLOW= ( 0.15, 0.5, 0.04 ) | ||
| % | ||
| % 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) | ||
| ADJ_OBJFUNC= DRAG | ||
| % | ||
| % Convective numerical method: (JST, LAX-FRIEDRICH, ROE-1ST_ORDER, | ||
| % ROE-2ND_ORDER) | ||
| CONV_NUM_METHOD_ADJ= JST | ||
| % | ||
| % Slope limiter: (NONE, 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_ADJ= ( 0.15, 0.5, 0.04 ) | ||
| % | ||
| % Reduction factor of the CFL coefficient in the adjoint problem | ||
| ADJ_CFL_REDUCTION= 0.25 | ||
| % | ||
| % Limit value for the adjoint variable | ||
| ADJ_LIMIT= 1E6 | ||
| % | ||
| % Remove sharp edges from the sensitivity evaluation (NO, YES) | ||
| SENS_REMOVE_SHARP= YES | ||
| % | ||
| % Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT) | ||
| TIME_DISCRE_ADJ= EULER_IMPLICIT | ||
|
|
||
| % --------------------------- PARTITIONING STRATEGY ---------------------------% | ||
| % | ||
| % Write a tecplot file for each partition (NO, YES) | ||
| VISUALIZE_PART= NO | ||
|
|
||
| % ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------% | ||
| % | ||
| % Airfoil sections definition, Ycoord (root, tip) | ||
| GEO_SECTION_LIMIT= (0.0806, 1.1284) | ||
| % | ||
| % Geometrical evaluation mode (FUNCTION, GRADIENT) | ||
| GEO_MODE= FUNCTION | ||
|
|
||
| % --------------------------- CONVERGENCE PARAMETERS --------------------------& | ||
| % | ||
| % Convergence criteria (CAUCHY, RESIDUAL) | ||
| CONV_CRITERIA= RESIDUAL | ||
| % | ||
| % 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= -5.70 | ||
| % | ||
| % Start convergence criteria at iteration number | ||
| STARTCONV_ITER= 100 | ||
| % | ||
| % Number of elements to apply the criteria | ||
| CAUCHY_ELEMS= 100 | ||
| % | ||
| % Epsilon to control the series convergence | ||
| CAUCHY_EPS= 1E-10 | ||
| % | ||
| % Direct function to apply the convergence criteria (LIFT, DRAG, NEARFIELD_PRESS) | ||
| CAUCHY_FUNC_FLOW= DRAG | ||
| % | ||
| % Adjoint function to apply the convergence criteria (SENS_GEOMETRY, SENS_MACH) | ||
| CAUCHY_FUNC_ADJ= SENS_GEOMETRY | ||
| % | ||
| % Epsilon for full multigrid method evaluation | ||
| FULLMG_CAUCHY_EPS= 1E-4 | ||
|
|
||
| % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% | ||
| % Mesh input file | ||
| MESH_FILENAME= mesh_ONERAM6_inv.su2 | ||
| % | ||
| % Mesh output file | ||
| 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 | ||
| % | ||
| % Mesh input file format (SU2) | ||
| MESH_FORMAT= SU2 | ||
| % | ||
| % Output file format (PARAVIEW, TECPLOT) | ||
| OUTPUT_FORMAT= TECPLOT | ||
| % | ||
| % Output file convergence history | ||
| 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= 500 | ||
| % | ||
| % Writing solution file frequency for physical time steps (dual time) | ||
| WRT_SOL_FREQ_DUALTIME= 1 | ||
| % | ||
| % Writing convergence history frequency | ||
| WRT_CON_FREQ= 1 | ||
| % | ||
| % Writing convergence history frequency (dual time, only written to screen) | ||
| WRT_CON_FREQ_DUALTIME= 10 | ||
| % | ||
| % Writing linear solver history frequency | ||
| WRT_LIN_CON_FREQ= 1 | ||
| % | ||
| % Output rind layers in the solution files | ||
| WRT_HALO= NO | ||
| % | ||
| % ----------------------- DESIGN VARIABLE PARAMETERS --------------------------% | ||
| % | ||
| % Kind of deformation (NO_DEFORMATION, HICKS_HENNE, PARABOLIC, NACA_4DIGITS, | ||
| % DISPLACEMENT, ROTATION, FFD_CONTROL_POINT, | ||
| % FFD_DIHEDRAL_ANGLE, FFD_TWIST_ANGLE, | ||
| % FFD_ROTATION, FFD_CAMBER, FFD_THICKNESS, FFD_VOLUME) | ||
| DV_KIND= NO_DEFORMATION | ||
| % | ||
| % Marker of the surface in which we are going apply the shape deformation | ||
| DV_MARKER= ( UPPER_SIDE, LOWER_SIDE, TIP ) | ||
| % | ||
| % Parameters of the shape deformation | ||
| % - FFD_CONTROL_POINT ( Chunk, i_Ind, j_Ind, k_Ind, x_Disp, y_Disp, z_Disp ) | ||
| % - FFD_DIHEDRAL_ANGLE ( Chunk, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) | ||
| % - FFD_TWIST_ANGLE ( Chunk, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) | ||
| % - FFD_ROTATION ( Chunk, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) | ||
| % - FFD_CAMBER ( Chunk, i_Ind, j_Ind ) | ||
| % - FFD_THICKNESS ( Chunk, i_Ind, j_Ind ) | ||
| % - FFD_VOLUME ( Chunk, i_Ind, j_Ind ) | ||
| DV_PARAM= ( 0, 1, 0, 0, 0.0, 0.0, 1.0 ) | ||
| % | ||
| % New value of the shape deformation | ||
| DV_VALUE= 0.0 | ||
|
|
||
| % ------------------------ GRID DEFORMATION PARAMETERS ------------------------% | ||
| % | ||
| % Grid deformation technique (SPRING, FEA) | ||
| GRID_DEFORM_METHOD= SPRING | ||
| % | ||
| % Visualize the deformation (NO, YES) | ||
| VISUALIZE_DEFORMATION= NO | ||
|
|
||
| % --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------% | ||
| % Available flow based objective functions or constraint functions | ||
| % DRAG, LIFT, SIDEFORCE, EFFICIENCY, | ||
| % FORCE_X, FORCE_Y, FORCE_Z, | ||
| % MOMENT_X, MOMENT_Y, MOMENT_Z, | ||
| % THRUST, TORQUE, FIGURE_OF_MERIT, | ||
| % EQUIVALENT_AREA, NEARFIELD_PRESSURE, | ||
| % FREE_SURFACE | ||
| % | ||
| % Available geometrical based objective functions or constraint functions | ||
| % MAX_THICKNESS, 1/4_THICKNESS, 1/2_THICKNESS, 3/4_THICKNESS, AREA, AOA, CHORD, | ||
| % MAX_THICKNESS_SEC1, MAX_THICKNESS_SEC2, MAX_THICKNESS_SEC3, MAX_THICKNESS_SEC4, MAX_THICKNESS_SEC5, | ||
| % 1/4_THICKNESS_SEC1, 1/4_THICKNESS_SEC2, 1/4_THICKNESS_SEC3, 1/4_THICKNESS_SEC4, 1/4_THICKNESS_SEC5, | ||
| % 1/2_THICKNESS_SEC1, 1/2_THICKNESS_SEC2, 1/2_THICKNESS_SEC3, 1/2_THICKNESS_SEC4, 1/2_THICKNESS_SEC5, | ||
| % 3/4_THICKNESS_SEC1, 3/4_THICKNESS_SEC2, 3/4_THICKNESS_SEC3, 3/4_THICKNESS_SEC4, 3/4_THICKNESS_SEC5, | ||
| % AREA_SEC1, AREA_SEC2, AREA_SEC3, AREA_SEC4, AREA_SEC5, | ||
| % AOA_SEC1, AOA_SEC2, AOA_SEC3, AOA_SEC4, AOA_SEC5, | ||
| % CHORD_SEC1, CHORD_SEC2, CHORD_SEC3, CHORD_SEC4, CHORD_SEC5 | ||
| % | ||
| % Available design variables | ||
| % HICKS_HENNE ( 1, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc ) | ||
| % COSINE_BUMP ( 2, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc, x_Size ) | ||
| % SPHERICAL ( 3, Scale | Mark. List | ControlPoint_Index, Theta_Disp, R_Disp ) | ||
| % NACA_4DIGITS ( 4, Scale | Mark. List | 1st digit, 2nd digit, 3rd and 4th digit ) | ||
| % DISPLACEMENT ( 5, Scale | Mark. List | x_Disp, y_Disp, z_Disp ) | ||
| % ROTATION ( 6, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn ) | ||
| % FFD_CONTROL_POINT ( 7, Scale | Mark. List | Chunk, i_Ind, j_Ind, k_Ind, x_Mov, y_Mov, z_Mov ) | ||
| % FFD_DIHEDRAL_ANGLE ( 8, Scale | Mark. List | Chunk, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) | ||
| % FFD_TWIST_ANGLE ( 9, Scale | Mark. List | Chunk, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) | ||
| % FFD_ROTATION ( 10, Scale | Mark. List | Chunk, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End ) | ||
| % FFD_CAMBER ( 11, Scale | Mark. List | Chunk, i_Ind, j_Ind ) | ||
| % FFD_THICKNESS ( 12, Scale | Mark. List | Chunk, i_Ind, j_Ind ) | ||
| % FFD_VOLUME ( 13, Scale | Mark. List | Chunk, i_Ind, j_Ind ) | ||
| % FOURIER ( 14, Scale | Mark. List | Lower(0)/Upper(1) side, index, cos(0)/sin(1) ) | ||
| % | ||
| % Optimization objective function with scaling factor | ||
| % ex= Objective * Scale | ||
| OPT_OBJECTIVE= DRAG * 0.1 | ||
| % | ||
| % Optimization constraint functions with scaling factors, separated by semicolons | ||
| % ex= (Objective = Value ) * Scale, use '>','<','=' | ||
| OPT_CONSTRAINT= (LIFT > 0.2864) * 0.1; (MAX_THICKNESS_SEC1 > 0.0570) * 0.1; (MAX_THICKNESS_SEC2 > 0.0513) * 0.1; (MAX_THICKNESS_SEC3 > 0.0457) * 0.1; (MAX_THICKNESS_SEC4 > 0.0399) * 0.1; (MAX_THICKNESS_SEC5 > 0.0343) * 0.1 | ||
| % | ||
| % Optimization design variables, separated by semicolons | ||
| DEFINITION_DV= ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 0, 0, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 1, 0, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 2, 0, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 3, 0, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 4, 0, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 0, 1, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 1, 1, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 2, 1, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 3, 1, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 4, 1, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 0, 2, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 1, 2, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 2, 2, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 3, 2, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 4, 2, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 0, 3, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 1, 3, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 2, 3, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 3, 3, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 4, 3, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 0, 4, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 1, 4, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 2, 4, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 3, 4, 1, 0.0, 0.0, 1.0 ); ( 7, 1.0 | UPPER_SIDE, LOWER_SIDE, TIP | 0, 4, 4, 1, 0.0, 0.0, 1.0 ); |