An Attempt for Suppression of Wing-Tip Vortex Using Plasma Actuators

Hasebe, Hitomi; Naka, Yoshifumi; Fukagata, Koji

doi:10.1299/jfst.6.976

Cited by 20 publications

(12 citation statements)

References 27 publications

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“…Caruana et al (2009) used the plasma jet as a synthetic jet, and Tan et al (2015) showed the heat transfer enhancement of impinging jet by a synthetic jet. By plasma jet (Touchard, 2008, Hasebe et al, 2011, Caruana et al, 2013:…”

Section: Active Jet Flow Controlmentioning

confidence: 99%

Passive flow control of jets

Shakouchi

2020

Mechanical Engineering Reviews

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One of the major purposes of fluid mechanics and engineering is to reduce the flow resistance caused by flow friction, flow separation, vortex generation, and other factors. To reduce or eliminate flow resistance, in general, flow control is performed either passively or actively. Passive flow control is performed by changing the flow channel or object shape a little and reducing the total flow resistance. On the contrary, active flow control uses a device requiring power, but it can perform various complex flow controls. In this paper, the passive flow control of jets is examined with flow characteristics, control methods, and some applications because jet flows include the essence of fluid dynamics, such as, boundary layer flow, turbulent flow, shear flow, and flow mixing. In particular, the effects of the nozzle shape, the tab, rib and vortex generator, and the orifice or notched orifice on the flow characteristics of sub-and supersonic jets are examined. Furthermore, the control and suppression of high speed jet noise by a chevron nozzle, some examples of active flow control, and other areas are examined. Globular formation of fine solid particles by flow control, lift control of airplane wings, and the flow control of a NOTAR helicopter without tail rotor are also addressed.

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Section: Active Jet Flow Controlmentioning

confidence: 99%

Passive flow control of jets

Shakouchi

2020

Mechanical Engineering Reviews

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“…Dielectric Barrier Discharge)を用いた，DBD プラズマアクチュエータがある．これは電磁気現象を利用するので従来の機械システムによる流体の制御方法よりレスポンスが早いことや軽量であることから注目されている．これまでプラズマアクチュエータを流体制御に用いた研究は，主に航空宇宙分野の翼周りにおいて研究されており，さらには鈍頭物体などの後流制御に応用されている (1)(2)(3)(4)(5)(6) ．噴流の研究においては，円形電極を設置し，間欠的にアクチュエータを駆動させることによって，周期的渦輪を発生させる方法…”

Section: 緒言近年，様々な流体の制御デバイスが考案されており，動的制御方法の一つとして，誘電体バリヤ放電(Dbdunclassified

Jet Control by a Coaxial Type DBD Plasma Actuator

Miyagi

Ohnishi²,

Asakura³

et al. 2013

Trans.JSME, Ser.B

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This study investigated the use of a coaxial dielectric barrier discharge plasma actuator at a nozzle exit for jet diffusion control. In order to achieve enhanced mixing of the primary jet flow, the influence of the input voltage and frequency to the plasma actuator was examined. In the case of continuous operating, the secondary flow by the induced flow using coaxial plasma actuator is able to adjust the velocity gradient of the free shear layer near the jet nozzle.Intermittent control using the plasma actuator was also attempted by varying the driving frequency and the duty ratio.Based on the results of a PIV analysis, the optimum conditions for jet diffusion control were found to be a driving frequency that matched the preferred frequency and a duty ratio at 50%.

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“…Many researchers have further investigated the potential of this device. As a result, plasma actuators have found many applications such as flow separation control for airfoils (Post and Corke, 2004), flow control around a circular cylinder (Jukes and Choi, 2009), wind turbine performance enhancement (Greenblat, et al, 2012) and the suppression of vortices (Hasebe, et al, 2011).…”

Section: Introductionmentioning

confidence: 99%

Control of leading edge separation on airfoil using DBD plasma actuator

Daud

Kozato

Kikuchi³

et al. 2014

JFST

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This study deals with the separation control of an airfoil when a dielectric barrier discharge (DBD) plasma actuator is mounted on its leading edge. The experiments were performed at Reynolds number, Re ≈ 67,000 in an external airflow of 10 m/s. The DBD plasma actuator was installed at x/c = 0.025 of a NACA0015 airfoil with a 100-mm chord and 150-mm width. Flow visualization, lift force and velocity measurements were conducted with on and off modes of the actuator (pulse-modulated drive). We found that the application of pulse modulation condition was able to delay a stall up to angle of attack α =17° compared to the Duty = 100% (α =15°). At α =17°, the maximum lift coefficient C l was obtained for a non-dimensional pulse modulation frequency St of 4.0. With an increase in α, the lift coefficient C l decreases sharply after reaching a maximum, which is entirely different from the case of St = 0.6, where the value of C l falls gradually. For a high angle of attack (α =18°) that exceeds the maximum C l , St = 0.6 produces a better lift improvement than when St = 4.0. Our results showed that the separation when St = 4.0 is larger than that when St = 0.6. In addition, we also found that there is an optimum actuation time of about 0.25 ms.

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An Attempt for Suppression of Wing-Tip Vortex Using Plasma Actuators

Cited by 20 publications

References 27 publications

Passive flow control of jets

Passive flow control of jets

Jet Control by a Coaxial Type DBD Plasma Actuator

Control of leading edge separation on airfoil using DBD plasma actuator

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