Flow control with multi-DBD plasma actuator on a delta wing

Muhammad Denni Kesuma; Ridho Irwansyah; James Julian; Adhika Satyadharma

doi:10.5109/4150513

Flow control with multi-DBD plasma actuator on a delta wing

Harinaldi, Muhammad Denni Kesuma, Ridho Irwansyah, James Julian, Adhika Satyadharma

Department of Mechanical Engineering

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

8 Citations (Scopus)

Abstract

In this study, an experiment was carried out to measure the performance of a delta wing with 65^o swept angle. The measurement of lift and drag on the delta wing with and without plasma actuator was the main focus of this research. Multi-DBD plasma actuator was implemented on top of the wing. The experiment was conducted in a wind tunnel with a free stream velocity of 5.74 m/s or at Reynolds number of 83000. The performance of the wing was positively affected by the use of plasma actuator, indicated by the increasing lift coefficient and the decreasing drag coefficient, as maximum increase of 0.078 in lift coefficient and 0.053 decrease in drag coefficient were obtained.

Original language	English
Pages (from-to)	602-608
Number of pages	7
Journal	Evergreen
Volume	7
Issue number	4
DOIs	https://doi.org/10.5109/4150513
Publication status	Published - 2020

Keywords

Actuator
Delta wing
Drag
Lift
Plasma

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10.5109/4150513

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title = "Flow control with multi-DBD plasma actuator on a delta wing",

abstract = "In this study, an experiment was carried out to measure the performance of a delta wing with 65o swept angle. The measurement of lift and drag on the delta wing with and without plasma actuator was the main focus of this research. Multi-DBD plasma actuator was implemented on top of the wing. The experiment was conducted in a wind tunnel with a free stream velocity of 5.74 m/s or at Reynolds number of 83000. The performance of the wing was positively affected by the use of plasma actuator, indicated by the increasing lift coefficient and the decreasing drag coefficient, as maximum increase of 0.078 in lift coefficient and 0.053 decrease in drag coefficient were obtained.",

keywords = "Actuator, Delta wing, Drag, Lift, Plasma",

author = "Harinaldi and Kesuma, {Muhammad Denni} and Ridho Irwansyah and James Julian and Adhika Satyadharma",

note = "Funding Information: The authors would like to thank Direktorat Riset dan Pengabdian Masyarakat (DRPM) Universitas Indonesia for funding this research through funding number NKB0300/UN2.R3.1/HKP.05.00/2019. Publisher Copyright: {\textcopyright} 2020, Novel Carbon Resource Sciences. All rights reserved. Copyright: Copyright 2021 Elsevier B.V., All rights reserved.",

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doi = "10.5109/4150513",

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AU - Harinaldi,

AU - Kesuma, Muhammad Denni

AU - Irwansyah, Ridho

AU - Julian, James

AU - Satyadharma, Adhika

N1 - Funding Information: The authors would like to thank Direktorat Riset dan Pengabdian Masyarakat (DRPM) Universitas Indonesia for funding this research through funding number NKB0300/UN2.R3.1/HKP.05.00/2019. Publisher Copyright: © 2020, Novel Carbon Resource Sciences. All rights reserved. Copyright: Copyright 2021 Elsevier B.V., All rights reserved.

PY - 2020

Y1 - 2020

N2 - In this study, an experiment was carried out to measure the performance of a delta wing with 65o swept angle. The measurement of lift and drag on the delta wing with and without plasma actuator was the main focus of this research. Multi-DBD plasma actuator was implemented on top of the wing. The experiment was conducted in a wind tunnel with a free stream velocity of 5.74 m/s or at Reynolds number of 83000. The performance of the wing was positively affected by the use of plasma actuator, indicated by the increasing lift coefficient and the decreasing drag coefficient, as maximum increase of 0.078 in lift coefficient and 0.053 decrease in drag coefficient were obtained.

AB - In this study, an experiment was carried out to measure the performance of a delta wing with 65o swept angle. The measurement of lift and drag on the delta wing with and without plasma actuator was the main focus of this research. Multi-DBD plasma actuator was implemented on top of the wing. The experiment was conducted in a wind tunnel with a free stream velocity of 5.74 m/s or at Reynolds number of 83000. The performance of the wing was positively affected by the use of plasma actuator, indicated by the increasing lift coefficient and the decreasing drag coefficient, as maximum increase of 0.078 in lift coefficient and 0.053 decrease in drag coefficient were obtained.

KW - Actuator

KW - Delta wing

KW - Drag

KW - Lift

KW - Plasma

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SP - 602

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JO - Evergreen

JF - Evergreen

IS - 4

ER -

Flow control with multi-DBD plasma actuator on a delta wing

Abstract

Keywords

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