An attempt for suppression of wing-tip vortex using plasma actuators

Hitomi Hasebe, Yoshitsugu Naka, Koji Fukagata

研究成果: Article査読

4 被引用数 (Scopus)

抄録

Influence of the flow induced by dielectric barrier discharge (DBD) plasma actuators on the wing-tip vortex is investigated numerically and experimentally. The plasma actuators are installed on the suction side of the NACA0012 airfoil and operated in blowing and suction modes. For the numerical simulation, direct numerical simulation (DNS) based on the finite-difference immersed-boundary method is used. The DNS shows that the circulation parameter, which measures the strength of wing-tip vortex, is reduced by blowing as well as suction. At the same time, however, the lift-to-drag ratio is found to decrease by the actuation. In the experiment, a wing model with plasma actuators is set inside the wind tunnel and the velocity components are measured using a PIV system. Although suppression of wing-tip vortex is not confirmed due to insufficient strength of actuation and insufficient length of messurement area, the change of streamwise mean velocity profile is found to be similar to that of DNS.

本文言語English
ページ(範囲)659-671
ページ数13
ジャーナルNihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B
77
775
DOI
出版ステータスPublished - 2011
外部発表はい

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Mechanical Engineering

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