Leading edge vortex flow control on a delta wing with dielectric barrier discharge plasma actuators

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Leading edge vortex flow control on a delta wing with dielectric barrier discharge plasma actuators

 

Author: Shen, Lu
Title: Leading edge vortex flow control on a delta wing with dielectric barrier discharge plasma actuators
Degree: M.Sc.
Year: 2014
Subject: Actuators.
Drone aircraft.
Hong Kong Polytechnic University -- Dissertations
Department: Faculty of Engineering
Pages: ix, 84 leaves : col. ill. ; 30 cm.
Language: English
InnoPac Record: http://library.polyu.edu.hk/record=b2748047
URI: http://theses.lib.polyu.edu.hk/handle/200/7440
Abstract: The application of single-dielectric barrier discharge (SDBD) plasma actuator on active flow control becomes popular in the last decade. This project aims to control actively a leading edge vortex on a highly swept full span delta wing at typical unmanned aerial vehicles (UAV) Reynolds number, by means of a SDBD plasma actuator supplied with a steady/ unsteady ac voltage. The experiments of the flat-arranged and leading-edge-arranged SDBD help understand the characteristics of SDBD and the flow structure of the SDBD induced flow. The smoke wire flow visualization shows that the plasma actuator implemented on one side significantly affects the leading edge vortexes at both sides, advance the break-down at the same side and delays the breakdown at the other side. This interesting phenomenon has not been observed in the literature before. The result of PIV measurement not only matches the result of smoke wire flow visualization but also provides details of the flow structure over the delta wing to understand the underlying mechanism. The result of force measurement shows that there is little effect on the lift with one SDBD control but a significant lift enhancement with double SDBD control. In summary, SDBD plasma actuator is a promising technologies in advancing the aerodynamic performance and maneuvering of a highly swept delta wing.

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