Numerical analysis of the ONERA-M6 wing with wind tunnel wall interference

Taisuke Nambu, Atsushi Hashimoto, Takashi Aoyama, Tetsuya Sato

研究成果: Article査読

5 被引用数 (Scopus)

抄録

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.

本文言語English
ページ(範囲)7-14
ページ数8
ジャーナルTransactions of the Japan Society for Aeronautical and Space Sciences
58
1
DOI
出版ステータスPublished - 2015

ASJC Scopus subject areas

  • 航空宇宙工学
  • 宇宙惑星科学

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