LES of transient flows controlled by DBD plasma actuator over a stalled airfoil

K. Asada, T. Nonomura, H. Aono, M. Sato, K. Okada, K. Fujii

Research output: Contribution to journalArticlepeer-review

22 Citations (Scopus)

Abstract

Large-eddy simulations (LES) are employed to understand the flow field over a NACA 0015 airfoil controlled by a dielectric barrier discharge (DBD) plasma actuator. The Suzen body force model is utilised to introduce the effect of the DBD plasma actuator. The Reynolds number is fixed at 63,000. Transient processes arising due to non-dimensional excitation frequencies of one and six are discussed. The time required to establish flow authority is between four and six characteristic times, independent of the excitation frequency. If the separation is suppressed, the initial flow conditions do not affect the quasi-steady state, and the lift coefficient of the higher frequency case converges very quickly. The transient states can be categorised into following three stages: (1) the lift and drag decreasing stage, (2) the lift recovery stage, and (3) the lift and drag converging stage. The development of vortices and their influence on control is delineated. The simulations show that in the initial transient state, separation of flow suppression is closely related to the development spanwise vortices while during the later, quasi-steady state, three-dimensional vortices become more important.

Original languageEnglish
Pages (from-to)215-229
Number of pages15
JournalInternational Journal of Computational Fluid Dynamics
Volume29
Issue number3-5
DOIs
Publication statusPublished - 2015 Mar 16
Externally publishedYes

Keywords

  • burst-mode actuation
  • compact finite difference scheme
  • dielectric barrier discharge plasma actuator
  • large-eddy simulation
  • separated flow control

ASJC Scopus subject areas

  • Computational Mechanics
  • Aerospace Engineering
  • Condensed Matter Physics
  • Energy Engineering and Power Technology
  • Mechanics of Materials
  • Mechanical Engineering

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