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

Hitomi Hasebe, Yoshitsugu Naka, Koji Fukagata

Research output: Contribution to journalArticle

3 Citations (Scopus)

Abstract

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.

Original languageEnglish
Pages (from-to)659-671
Number of pages13
JournalNihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B
Volume77
Issue number775
DOIs
Publication statusPublished - 2011 Dec 1
Externally publishedYes

    Fingerprint

Keywords

  • Flow control
  • Numerical simulation
  • PIV measurement
  • Plasma actuator
  • Wing-tip vortex

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Mechanical Engineering

Cite this