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.
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ASME-JSME-KSME 2011 Joint Fluids Engineering Conference
July 24–29, 2011
Hamamatsu, Japan
Conference Sponsors:
- Fluids Engineering Division
ISBN:
978-0-7918-4440-3
PROCEEDINGS PAPER
Computational Study of Aerodynamic Characteristics of an Airfoil With DBD Plasma Actuator
Kengo Asada,
Kengo Asada
The University of Tokyo, Sagamihara, Kanagawa, Japan
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Kozo Fujii
Kozo Fujii
Japan Aerospace Exploration Agency, Sagamihara, Kanagawa, Japan
Search for other works by this author on:
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
Published Online:
May 25, 2012
Citation
Asada, K, & Fujii, K. "Computational Study of Aerodynamic Characteristics of an Airfoil With DBD Plasma Actuator." Proceedings of the 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. pp. 3497-3505. ASME. https://doi.org/10.1115/AJK2011-15027
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