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

Taisuke Nambu, Atsushi Hashimoto, Takashi Aoyama, Tetsuya Sato

Research output: Contribution to journalArticlepeer-review

6 Citations (Scopus)


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.

Original languageEnglish
Pages (from-to)7-14
Number of pages8
JournalTransactions of the Japan Society for Aeronautical and Space Sciences
Issue number1
Publication statusPublished - 2015


  • Computational fluid dynamics
  • ONERA-M6 wing
  • Porous wall
  • Wall interference

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science


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