Investigation of Phase and Spacing Effects in Synthetic Jet Actuator Arrays

Liddle, Stephen; Crowther, William; Wood, N. J.

doi:10.2514/6.2005-107

Cited by 6 publications

(7 citation statements)

References 6 publications

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“…11. It is worth noting that the high chamber aspect ratio identified as optimal in the present work is inconsistent both with the geometry used for many experimental [2,3,4,[8][9][10][11] and CFD [31][32][33] related studies of SJA actuator performance and the schematic diagrams typically used by researchers to illustrate the operation of SJAs.…”

Section: Sja Characterization and Optimizationmentioning

confidence: 86%

“…There are many studies in the literature looking at the potential performance benefits of flow control in general and SJA applications in particular. However, due to the cost and complexity of undertaking flow control experiments or calculations at industrial scale, most of these studies tend to focus on the more fundamental fluid mechanics aspects [3][4][5][6][7][8][9][10][11][12]; there is therefore currently little reliable information on the overall performance benefit to a complete aircraft. In order to move the debate forwards, the present study focuses on careful evaluation of the cost side of the overall performance evaluation, which is presently a more tractable problem.…”

Section: Introductionmentioning

confidence: 99%

“…Actuator location used for case studies indicated by dashed line used for a number of previous studies within the laboratory[3,4] and the peak velocity obtained is around 50 m/s. The H/d 5 0.56 case represents the 'optimized' geometry from the present set of experiments and the peak velocity at approximately 110 m/s is double that achieved for the unoptimized case.…”

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confidence: 99%

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An evaluation of the mass and power scaling of synthetic jet actuator flow control technology for civil transport aircraft applications

Crowther

Gomes

2008

Proceedings of the Institution of Mechanical Engineers, Part I:

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This paper aims to develop understanding of the systems costs associated with the application of flow control systems to civil transport aircraft based on the use of electrically powered synthetic jet actuators (SJAs). The study is based on the development of a low-order mass model using estimated power specific masses of generation, management, distribution, and conversion subsystems; application of existing empirical rules for application of pneumatic boundary layer mixing flow control devices to determine the required fluid power for an A320 case study application; and characterization and optimization of lab-based SJA technology to establish realistic estimates for power conversion efficiency and actuator maximum authority. The peak velocity obtained from a velocity-optimized synthetic jet actuator was 130 m/s, at a corresponding power efficiency of 7 per cent. The highest power efficiency obtained was 14 per cent, corresponding to a peak velocity of 70 m/s. The power specific mass for the overall flow control system considered for the A320 application is estimated to be around 1 kg of system mass per kW of electrical power required, of which around 50 per cent is due to power generation and 30 per cent is due to power conversion (actuation).

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Section: Sja Characterization and Optimizationmentioning

confidence: 86%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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An evaluation of the mass and power scaling of synthetic jet actuator flow control technology for civil transport aircraft applications

Crowther

Gomes

2008

Proceedings of the Institution of Mechanical Engineers, Part I:

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“…They hypothesized that under this condition these two SJs are combined to form a stronger vortex structure. Liddle et al 14,15 investigated the effect of relative phase difference between the in-line twin SJs in a boundary layer using hot-wire measurements. The power spectral density (PSD) analysis of near-wall velocity in the mid-span plane reveals that the frequency corresponding to the major spectral peak coincides with the SJ operating frequency in most of the investigated cases, but at phase difference ∆φ = 270…”

Section: -2mentioning

confidence: 99%

Vortex dynamics of in-line twin synthetic jets in a laminar boundary layer

2015

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An experimental investigation is conducted on the vortices induced by twin synthetic jets (SJs) in line with a laminar boundary layer flow over a flat plate. The twin SJs operating at four different phase differences, i.e., Δϕ = 0°, 90°, 180°, and 270°, are visualized using a stereoscopic color dye visualization system and measured using a two-dimensional particle image velocimetry (PIV) system. It is found that depending on the phase difference of twin SJs, three types of vortex structures are produced. At Δϕ = 90°, the two hairpin vortices interact in a very constructive way in terms of the vortex size, strength, and celerity, forming one combined vortex. At Δϕ = 270°, the two individual hairpin vortices do not have much interaction, forming two completely separated hairpin vortices that behave like doubling the frequency of the single SJ case. At Δϕ = 0° and 180°, the two hairpin vortices produced by the twin SJ actuators are close enough, with the head of one hairpin vortex coupled with the legs of the other, forming partially interacting vortex structures. Quantitative analysis of the twin SJs is conducted, including the time histories of vortex circulation in the mid-span plane as well as a selected spanwise-wall-normal plane, and the influence of the twin SJs on the boundary layer flow filed. In addition, dynamic mode decomposition analysis of the PIV data is conducted to extract representative coherent structures. Through this study, a better understanding in the vortex dynamics associated with the interaction of in-line twin SJs in laminar boundary layers is achieved, which provides useful information for future SJ-array applications.

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“…Therefore, the optimization design of synthetic jet actuator arrays has become more and more important to satisfy the "strength" and "micro-" requirements in given conditions [4]. There were some results that showed phase difference had great effect on the controlling ability of synthetic jet actuator array [6][7]. Take an example of adjacent synthetic jets, the exit flowfield characteristics exhibit differently with different phase difference.…”

Section: Introductionmentioning

confidence: 99%

Investigation of phase excitation effect on mixing control in coaxial jets

2009

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Detailed unsteady numerical simulation has been carried out to investigate the mechanism of adjacent synthetic jets and the influence of different phases on the mixing of coaxial jets. The results show the combined jet, formed by coupling the vortex pairs at the orifice of two adjacent actuators, can exhibit better controlling effect. Spanwise pressure difference appears because of the existence of phase difference between the left jet and right jet, which results in the variation of the combined jet. When the phase difference is greater than zero, mixing enhancement of coaxial jets can be achieved, but there are maximum phase difference and optimal phase difference. On the contrary, application of adjacent synthetic jets always leads to the mixing reduction when phase difference is less than zero.

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Investigation of Phase and Spacing Effects in Synthetic Jet Actuator Arrays

Cited by 6 publications

References 6 publications

An evaluation of the mass and power scaling of synthetic jet actuator flow control technology for civil transport aircraft applications

An evaluation of the mass and power scaling of synthetic jet actuator flow control technology for civil transport aircraft applications

Vortex dynamics of in-line twin synthetic jets in a laminar boundary layer

Investigation of phase excitation effect on mixing control in coaxial jets

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