Plasma-actuator burst-mode frequency effects on leading-edge flow-separation control at reynolds number 2.6 × 105

Hikaru Aono; Soshi Kawai; Taku Nonomura; Makoto Sato; Kozo Fujii; Koichi Okada

doi:10.2514/1.J055727

Plasma-actuator burst-mode frequency effects on leading-edge flow-separation control at reynolds number 2.6 × 10⁵

Hikaru Aono, Soshi Kawai, Taku Nonomura, Makoto Sato, Kozo Fujii, Koichi Okada

ENG - Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

22 Citations (Scopus)

Abstract

This paper investigates the control of leading-edge flow separation over an airfoil using a dielectric-barrier discharge plasma actuator. A chord-based Reynolds number and an angle of attack are 2.6 × 10⁵ and 18.8 deg, respectively. The flow around the stalled airfoil is computed by using large-eddy simulations. The body-force distribution-based plasma actuator model is adopted and set near the leading edge of the airfoil. Effects of a nondimensional burst frequency with a constant duty cycle onthe performance of flow control are studied. It isfound that, for the cases of the nondimensional burst frequencies 5, 10, 25, and 50, lift-to-drag ratios increase in comparison with that in the cases of the burst frequencies 1 and 100 and without the control. Controlled flow separates near the 30% chord from the leading edge due to adverse pressure gradient associated with the angleofattack. Mechanisms of suppression of the leading-edge flow separation in those cases are discussed.

Original language	English
Pages (from-to)	3789-3806
Number of pages	18
Journal	AIAA journal
Volume	55
Issue number	11
DOIs	https://doi.org/10.2514/1.J055727
Publication status	Published - 2017

ASJC Scopus subject areas

Aerospace Engineering

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10.2514/1.J055727

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@article{3504e8d6c6e8464aba63a1cf9d2eda9b,

title = "Plasma-actuator burst-mode frequency effects on leading-edge flow-separation control at reynolds number 2.6 × 105",

abstract = "This paper investigates the control of leading-edge flow separation over an airfoil using a dielectric-barrier discharge plasma actuator. A chord-based Reynolds number and an angle of attack are 2.6 × 105 and 18.8 deg, respectively. The flow around the stalled airfoil is computed by using large-eddy simulations. The body-force distribution-based plasma actuator model is adopted and set near the leading edge of the airfoil. Effects of a nondimensional burst frequency with a constant duty cycle onthe performance of flow control are studied. It isfound that, for the cases of the nondimensional burst frequencies 5, 10, 25, and 50, lift-to-drag ratios increase in comparison with that in the cases of the burst frequencies 1 and 100 and without the control. Controlled flow separates near the 30% chord from the leading edge due to adverse pressure gradient associated with the angleofattack. Mechanisms of suppression of the leading-edge flow separation in those cases are discussed.",

author = "Hikaru Aono and Soshi Kawai and Taku Nonomura and Makoto Sato and Kozo Fujii and Koichi Okada",

note = "Funding Information: This research used computational resources of the K computer and other computers of the high-performance computing infrastructure (HPCI) system provided by the RIKEN Advance Institute for Computational Science and the Information Technology Center, University of Tokyo, through the HPCI System Research Project (Project ID: hp120296, hp130001, hp140207, and hp150219). This work was also supported by JSPS Grant-in-Aid for Scientific Research No. 15H02324. We would like to thank Satoshi Sekimoto for providing the experimental data of the no-control case. H. Aono would like to thank Chang-Kwon Kang for careful checking of the manuscript. Publisher Copyright: Copyright {\textcopyright} 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.",

year = "2017",

doi = "10.2514/1.J055727",

language = "English",

volume = "55",

pages = "3789--3806",

journal = "AIAA Journal",

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publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

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T1 - Plasma-actuator burst-mode frequency effects on leading-edge flow-separation control at reynolds number 2.6 × 105

AU - Aono, Hikaru

AU - Kawai, Soshi

AU - Nonomura, Taku

AU - Sato, Makoto

AU - Fujii, Kozo

AU - Okada, Koichi

N1 - Funding Information: This research used computational resources of the K computer and other computers of the high-performance computing infrastructure (HPCI) system provided by the RIKEN Advance Institute for Computational Science and the Information Technology Center, University of Tokyo, through the HPCI System Research Project (Project ID: hp120296, hp130001, hp140207, and hp150219). This work was also supported by JSPS Grant-in-Aid for Scientific Research No. 15H02324. We would like to thank Satoshi Sekimoto for providing the experimental data of the no-control case. H. Aono would like to thank Chang-Kwon Kang for careful checking of the manuscript. Publisher Copyright: Copyright © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

PY - 2017

Y1 - 2017

N2 - This paper investigates the control of leading-edge flow separation over an airfoil using a dielectric-barrier discharge plasma actuator. A chord-based Reynolds number and an angle of attack are 2.6 × 105 and 18.8 deg, respectively. The flow around the stalled airfoil is computed by using large-eddy simulations. The body-force distribution-based plasma actuator model is adopted and set near the leading edge of the airfoil. Effects of a nondimensional burst frequency with a constant duty cycle onthe performance of flow control are studied. It isfound that, for the cases of the nondimensional burst frequencies 5, 10, 25, and 50, lift-to-drag ratios increase in comparison with that in the cases of the burst frequencies 1 and 100 and without the control. Controlled flow separates near the 30% chord from the leading edge due to adverse pressure gradient associated with the angleofattack. Mechanisms of suppression of the leading-edge flow separation in those cases are discussed.

AB - This paper investigates the control of leading-edge flow separation over an airfoil using a dielectric-barrier discharge plasma actuator. A chord-based Reynolds number and an angle of attack are 2.6 × 105 and 18.8 deg, respectively. The flow around the stalled airfoil is computed by using large-eddy simulations. The body-force distribution-based plasma actuator model is adopted and set near the leading edge of the airfoil. Effects of a nondimensional burst frequency with a constant duty cycle onthe performance of flow control are studied. It isfound that, for the cases of the nondimensional burst frequencies 5, 10, 25, and 50, lift-to-drag ratios increase in comparison with that in the cases of the burst frequencies 1 and 100 and without the control. Controlled flow separates near the 30% chord from the leading edge due to adverse pressure gradient associated with the angleofattack. Mechanisms of suppression of the leading-edge flow separation in those cases are discussed.

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Plasma-actuator burst-mode frequency effects on leading-edge flow-separation control at reynolds number 2.6 × 10⁵

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