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Computational Study of Aerodynamic Characteristics of an Airfoil With DBD Plasma Actuator

[+] Author Affiliations
Kengo Asada

The University of Tokyo, Sagamihara, Kanagawa, Japan

Kozo Fujii

Japan Aerospace Exploration Agency, Sagamihara, Kanagawa, Japan

Paper No. AJK2011-15027, pp. 3497-3505; 9 pages
doi:10.1115/AJK2011-15027
From:
  • ASME-JSME-KSME 2011 Joint Fluids Engineering Conference
  • ASME-JSME-KSME 2011 Joint Fluids Engineering Conference: Volume 1, Symposia – Parts A, B, C, and D
  • Hamamatsu, Japan, July 24–29, 2011
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 978-0-7918-4440-3
  • Copyright © 2011 by ASME

abstract

The relation between aerodynamic characteristics and the effectiveness of separation control with the DBD plasma actuator over the airfoil are discussed. The flow-fields around the NACA0015 airfoil are simulated with implicit large-eddy simulation using compact difference scheme. The normal mode generates moderately separated region over the airfoil and gains lift by negative pressure at the vortex center. The burst mode with nondimensional burst frequency of 1 enhances the vortex shedding from the separation shear layer and avoid the massive separation from the leading edge. However, the lift coefficient oscillate very much, in this case. The burst mode with nondimensional burst frequency of 6 improves the airfoil performance by suppressing the separation region. These facts indicate that the unsteady aerodynamic characteristics must be discussed when the effectiveness of separation control is evaluated.

Copyright © 2011 by ASME

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