FreeCASE - Free(dom) Computational AeroServoElasticity
Last update:
January 15. 2016 14:05:15

AGARD 445.6 wing

In this section we present the numerical results of Code_Aster solver for a structural test problem, such as the numerical set-up 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 n3
    • NACA 65A004 airfoil parallel to X axis
    • Root chord cr = 0.558 m
    • Half-wing 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 set-up 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.



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