AGARD 445.6 wingIn this section we present the numerical results of Code_Aster
solver for a structural test problem, such as the numerical setup with the genetic optimizer GenOpt written in SciLab of a FEM structural model which best fits the Ground Vibration Test experimental data.
Problem definition Domain:
 AGARD 445.6 weakened experimental model n°3
 NACA 65A004 airfoil parallel to X axis
 Root chord cr = 0.558 m
 Halfwing span b = 0.762 m
 Quarter chord sweepback angle Lambda = 45 deg
 Aspect ratio AR = 1.65
 Taper ratio lambda = 0.66
 Material:
 Laminated mahogany
 Density rho = 381.98 kg/m^3
 Parallel Young's modulus Ep = 3.151e9 Pa
 Orthogonal Young's modulus Eo = 4.162e8 Pa
 Tangential modulus G = 4.392e8 Pa
 Poisson's coefficient nu = 0.31
 Boundary conditions:
 Fixed translations and rotations at the root section y = 0 m
Figure: Problem definition. FEM discretization Space discretization:
 Uniform mesh of DKT 2D triangular plate elements
 # of TRIA3 elements Ne = 200
 # of COOR_3D nodes Nn = 121
Figure: Computational grid. Numerical results Comparison with Ground Vibration Test experimental data and with MSC.Nastran solver
 Single iteration CPUtime = 3.52 s on ASUS M6000 notebook PC with Intel Pentium M 2.0 GHz CPU, 1 Gbyte RAM, 2 Mbyte L2 cache
Figure: Offset between setup FEM model modal analysis and Ground Vibration Test experimental data.
Download AgardWingFEM.tar.gz test problem folder. Uncompress this archive in the $HOME folder and execute ~/Aster/ASTK/ASTK_SERV/bin/as_run ./AgardWingFEM.export from terminal to start the simulation. The AgardWingFEM.comm file is automatically created by the genetic optimizer GenOpt written in SciLab. Download.
