Numerical Analysis of the ONERA-M6 Wing with Wind Tunnel Wall Interference

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  • NAMBU Taisuke
    Department of Applied Mechanics, Waseda University
  • HASHIMOTO Atsushi
    Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
  • AOYAMA Takashi
    Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
  • SATO Tetsuya
    Department of Applied Mechanics, Waseda University

Bibliographic Information

Published
2015
DOI
  • 10.2322/tjsass.58.7
Publisher
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

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Description

The flow around an ONERA-M6 wing, including the effect of wind tunnel wall interference, is computed using CFD analysis with a porous wall model. The computational domain sets porous walls at the top and bottom of the wing section similar to actual wind tunnel experiments. The computational result captures almost the same shock wave shape as the wind tunnel. This could not be computed exactly in previous works that did not include wall effects. The interference of the porous walls reduces the Mach number and attack angle of the flow, and these effects alter the swept angle of front shock wave and the location of rear shock wave. The aerodynamics coefficients are also affected by the wall interference. The lift coefficient becomes smaller due to the reduction in attack angle. The lower Mach number decreases the drag coefficient, while the reduction in attack angle causes additional drag by a mechanism similar to induced drag.

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