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Flow control over the trailing edge of a NACA0015 aerofoil by the effect of a DBD plasma-induced vertical flow

Published online by Cambridge University Press:  17 December 2025

H. Mahdavi Open the ORCID record for H. Mahdavi [Opens in a new window] ,
R. Abdollahi  and
M. Mani
H. Mahdavi*
Affiliation:
Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran
R. Abdollahi
Affiliation:
Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran
M. Mani
Affiliation:
Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran
*
Corresponding author: Hoda Mahdavi; Email: hoda.mahdavi65@gmail.com
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Abstract

The electrohydrodynamic force of a surface dielectric barrier discharge (SDBD) has been well-developed for flow control applications during recent decades. In the present paper, a geometrical modification of the SDBD plasma actuator has been applied to induce a vectorised normal flow at the trailing edge of a NACA0015 aerofoil. The pitot-tube velocity measurements of the normal jet along its propagation direction revealed formation of vortices at the centre of the electrode distance played a role in flow control authority of the jet. The aerodynamic operation of the double-SDBD structure as a virtual flap was assessed versus a single counter-flow jet of a floating structure at pre- and post-stall angles of attack at low Reynolds numbers. It was found that at small angles of attack, the steady counter-flow gives the most effectiveness of lift enhancement in low velocity, whereas in the higher velocity the unsteady one results in more efficacy. The efficiency of both steady and unsteady normal jets increased considerably at high angles such that a lift coefficient improvement of 38% was achieved at $\alpha = 14^\circ $. In the higher velocity, the plasma induced vertical flow acts like a Gurney flap, causing lift increase at high angles by affecting the vortical structures at the trailing edge. Evaluating the obtained results recommended employment of the induced normal flow as a virtual flap at high angles of attack in the unsteady actuation mode.

Keywords

DBD plasma actuatorfloating structureflow controltrailing edgeunsteady excitationvectorized normal flow

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Type
Research Article
Information
The Aeronautical Journal , First View , pp. 1 - 25
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Copyright
© The Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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