Electrohydrodynamic Flow Control with a Glow-Discharge Surface Plasma

Roth, J. Reece; Sherman, D.M.; Wilkinson, Stephen

doi:10.2514/2.1110

Cited by 473 publications

(102 citation statements)

References 4 publications

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“…1 Hence, any method for reducing this drag, including but not limited to controlling surface receptivity and fluidic actuation, can have profound influence in transportation applications. 2 Ever since its first reported success, 3 plasma actuators have been extensively investigated for improving authority of flow control but with limited success due to their inherent near wall momentum/heat injection method. Such actuators produce a high gradient at the wall limiting an effective control.…”

Section: Introductionmentioning

confidence: 99%

Dielectric barrier discharge actuator for vehicle drag reduction at highway speeds

et al. 2016

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We propose and demonstrate reduction of aerodynamic drag for a realistic geometry at highway speeds using serpentine dielectric barrier discharge actuators. A comparable linear plasma actuator fails to reduce the drag at these speeds. Experimental data collected for linear and serpentine plasma actuators under quiescent operating conditions show that the serpentine design has profound effect on near wall flow structure and resulting drag. For certain actuator arrangement, the measured drag reduced by over 14% at 26.8 m/s (60 mph) and over 10% at 31.3 m/s (70 mph) opening up realistic possibility of reasonable energy savings for full scale ground vehicles. In addition, the power consumption data and drag reduction effectiveness for different input signals are also presented.

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Section: Introductionmentioning

confidence: 99%

Dielectric barrier discharge actuator for vehicle drag reduction at highway speeds

et al. 2016

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“…This has also motivated literature focused on developing computational models to solve the EHD governing equations [12][13][14][15][16][17]. In aerospace engineering, research efforts have focused on using dielectric barrier discharges (DBDs) to provide aerodynamic flow control to prevent subsonic boundary layer separation over aerofoils [18][19][20]. However, few studies in the literature have assessed the use of ionic winds in propulsion applications.…”

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confidence: 99%

Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Gilmore

Barrett

2015

Proc. R. Soc. A.

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ResearchCite this article: Gilmore CK, Barrett SRH. 2015 Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion. Proc. R. Soc Previous work has characterized electrohydrodynamic (EHD) thruster performance, determining that thrust-to-power ratios are comparable with that of conventional propulsion at the laboratory scale. Achievable thrust density of EHD propulsion has yet to be experimentally quantified and could be a limiting factor in its application. In this paper, we quantify the achievable thrust density for a wire-to-cylinder electrode geometry using positive corona discharges for electrode pairs operating in parallel and in series. Geometric parameters, including the non-dimensional inter-pair and stage spacings, are varied, and the effect on current and thrust is measured. We estimate a maximum thrust per unit area of 3.3 N m −2 and a maximum thrust per unit volume of 15 N m −3 , which we compare with the characteristic thrust density of a range of aircraft. We find that trade-offs exist between thrust density and the achieved thrust-to-power ratio, where increases in the former through either increased power input or pair packing density lead to decreases in the latter. We conclude that EHD propulsion has the potential to be viable from both an energy efficiency perspective (our previous study) and a thrust density perspective (this paper), with the greatest likelihood of viability for smaller aircraft such as unmanned aerial vehicles.

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“…Amongst various flow control methods, plasma devices have many positive characteristics. 1 They have been applied from subsonic to supersonic to hypersonic flow regimes. Specifically, extensive studies have focused on plasma control of subsonic flows.…”

Section: Introductionmentioning

confidence: 99%

Effect of dielectric barrier discharge plasma actuators on non-equilibrium hypersonic flows

Bhatia

Roy

Gosse

2014

Journal of Applied Physics

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Electrohydrodynamic Flow Control with a Glow-Discharge Surface Plasma

Cited by 473 publications

References 4 publications

Dielectric barrier discharge actuator for vehicle drag reduction at highway speeds

Dielectric barrier discharge actuator for vehicle drag reduction at highway speeds

Electrohydrodynamic thrust density using positive corona-induced ionic winds for in-atmosphere propulsion

Effect of dielectric barrier discharge plasma actuators on non-equilibrium hypersonic flows

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