The Attenuation of Cavity Tones Using Plasma Actuators

Chan, Sammie; Zhang, Xin; Gabriel, S.B.

doi:10.2514/6.2005-2802

Cited by 10 publications

(12 citation statements)

References 11 publications

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“…In [15], Corke et al study the leading edge separation control on a NACA 0015 airfoil and delay the stall angle by up to 7 degrees using both the unsteady and steady effects of the actuator with the maximum performance achieved at a Strouhal number (calculated based on the convection time-scale of the flow past the wing and the duty-cycle frequency) of one. Similar plasma-based actuation was used for the control of dynamic stall on oscillating airfoils [15].Chan [16] applied plasma-based EHD flow control in the study of acoustic effects in subsonic cavity flows. There have also been efforts to use plasmabased actuators in the context of turbulent boundary layer flow control [17].…”

Section: Introductionmentioning

confidence: 99%

Low-Reynolds Number Flow Control Using Dielectric Barrier Discharge-Based Actuators

Jayaraman¹,

Lian²,

Shyy³

2007

37th AIAA Fluid Dynamics Conference and Exhibit

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Dielectric Barrier Discharges (DBD), operated at KHz and KV range, can create athermal plasma via collision processes and induce near wall jet. In this paper, we investigate the potential of using DBD to conduct flow control at low Reynolds numbers, motivated by micro air vehicle (MAV) applications. A previously developed computational methodology, based on the e N transition model and the k-turbulence closure is adopted. The effects of actuators on the flow fields are represented with a body force model in the momentum equations. The flow control over an airfoil SD7003 at the chord Reynolds number of 6×10 4 is the focus of the present study. Specifically, we investigate both co-flow and counter-flow actuation strategies. The co-flow approach offers momentum enhancement via favorable pressure gradient in the near wall region while the counter flow approach can trigger earlier separation and transition by introducing adverse pressure gradients. The aerodynamic performance including lift and drag coefficients over a broad range of angle of attack (4 0-18 0) is studied, showing that improved lift and drag characteristics can be realized with DBD concepts for low Reynolds number aerodynamics.

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Section: Introductionmentioning

confidence: 99%

Low-Reynolds Number Flow Control Using Dielectric Barrier Discharge-Based Actuators

Jayaraman¹,

Lian²,

Shyy³

2007

37th AIAA Fluid Dynamics Conference and Exhibit

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“…The intermittence of discrete vortices under spanwise actuation was already discussed in our previous work. 18 In this work, we also investigated the flow field at z = 0 mm, where the large-scale vortical structures were found to be absent in the shear layer in almost all images ͓see Fig. 12͑f͔͒.…”

Section: Piv Resultsmentioning

confidence: 99%

Streamwise and spanwise plasma actuators for flow-induced cavity noise control

Huang

Zhang

2008

Physics of Fluids

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Plasma actuators operating in atmospheric air can induce a body force through collisions between electrically charged particles and neutral air molecules by an externally applied electric field. The fast response and the simple structure make the plasma actuator a promising option in aerospace applications. In this work, experiments were performed with several alternative current excited plasma ͑streamwise and spanwise͒ actuators to control flow-induced noise from a cavity. It was found that the streamwise actuator induced three-dimensional variations in the shear layer. The spanwise actuator, however, has little influence on the global flow field. As a result, the streamwise actuator is more effective than the spanwise actuator in cavity noise attenuation.

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“…More details of the AC power supply and the plasma actuators can be found in literatures. [3][4][5][6] (a) Figure 1). Other configurations were also extensively tested.…”

Section: Experimental Methodsmentioning

confidence: 99%

“…Plasma actuators, operating in atmospheric pressure air condition, hold the potential to reduce flow-induced noise through modifying aerodynamic flow field. Some recent work [3][4][5][6] have demonstrated the potential of using the dielectric barrier discharge (DBD) plasma actuators 7 to attenuate the tonal noise of a cavity that is similar to a landing gear bay.…”

Section: Introductionmentioning

confidence: 99%

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Bluff Body Noise and Flow Control with Atmospheric Plasma Actuators

Huang

Zhang

Gabriel

2008

14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference)

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Plasma actuators operating in atmospheric air were employed to modify aerodynamic flow over a bluff body. The model consisted of a cylinder and a strut that was installed on the trailing half side of the cylinder. The objective was to reduce the broadband noise that is mainly generated by the impingement of the cylinder wake on the strut. The plasma actuators were configured to produce dielectric barrier discharges, through which the flow separation from the cylinder was enhanced. As a result the wake-strut interaction was reduced, leading to the attenuation of broadband noise. The noise and flow control performance with the plasma actuators were studied in an anechoic chamber facility as well as a wind tunnel facility by examining sound pressure and mean flow field respectively. With the current plasma actuators, it was found that there was 1 dB reduction in overall sound pressure level at a free stream speed of 30 m/s, and the wake speed impinging on the strut was reduced. A possible solution to improve the broadband noise attenuation performance is discussed at the end of this paper.

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The Attenuation of Cavity Tones Using Plasma Actuators

Cited by 10 publications

References 11 publications

Low-Reynolds Number Flow Control Using Dielectric Barrier Discharge-Based Actuators

Low-Reynolds Number Flow Control Using Dielectric Barrier Discharge-Based Actuators

Streamwise and spanwise plasma actuators for flow-induced cavity noise control

Bluff Body Noise and Flow Control with Atmospheric Plasma Actuators

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