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

ONERA M6 wing

In this section we present the numerical results of AeroFoam solver for a 3D aerodynamic test problem, such as the inviscid compressible unsteady flow around a ONERA M6 wing.

Problem definition

  • Domain:
    • Internal ONERA M6 wing subdomain
    • External hexahedral subdomain of size 11 m x 5 m x 10 m
  • Material:
    • Polytropic Ideal Gas (PIG)
    • Specific heat ratio gamma = 1.4
    • Gas thermodynamic constant R = 287.05 J/kgK
  • Initial conditions: 
    • Thermodynamic pressure Poo = 31500 Pa
    • Temperature Too = 255.6 K
    • Mach number Moo = 0.84
    • Angle of attack alpha = 3.04 deg
  • Boundary conditions:
    • Slip boundary conditions on internal subdomain
    • SymmetryPlane boundary conditions on symmetry plane
    • Riemann boundary conditions on external subdomain


Figure: ONERA M6 wing subdomain geometry.

Space and time discretization

  • Space discretization:
    • Mesh created with GAMBIT
    • # of tetrahedral cells Nv = 341797
    • # of nodes Nn = 72791
  • Time discretization:
    • Total simulation time endTime = 0.0185 s
    • Timestep deltaT = 5e-7 s
    • Maximum Courant number maxCo =  1.95


Figure:
Computational grid.

Numerical results

  • Comparison with FLUENT solver and AGARD 138 report experimental results
  • Single iteration CPUtime = 3.48 s on AMD64 3500+ desktop PC with AMD Athlon 64 2.2 GHz CPU, 1 Gbyte RAM, 512 Kbyte L2 cache


Figure: Thermodynamic pressure P contours.



Figure:
Pressure coefficient Cp distribution.

Download

  • ONERAM6.tar.gz test problem folder. Uncompress this archive in the OpenFOAM work folder and execute AeroFoam . ONERAM6_340k_M084_a3 from terminal to start the simulation. Download.



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