Mechanisms of Control Authority by Nanosecond Pulsed Dielectric Barrier Discharge Actuators on Flow Separation

Skourides, Christoforos; Nyfantis, Dimitrios; Leyland, Pénélope; Bosse, H. G.; Ott, Peter

doi:10.3390/app9152989

Cited by 4 publications

(2 citation statements)

References 21 publications

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“…where c is the chord length of the airfoil, and u ∞ is the freestream velocity. Skourides et al [20] applied nanosecond-pulse DBD-PA [21] on a NACA0015 airfoil under post-stall angle and a higher Reynolds number than this study and also concluded that F + = 1 and 2 were effective. Our former studies showed that the burst-mode actuation is particularly effective at angles of attack close to the stall angle (because the separated shear layer is closely located near the airfoil surface, and specific burst frequencies are effective for promoting transition) [11,12,16].…”

Section: Introductionmentioning

confidence: 43%

In-Flight Demonstration of Stall Improvement Using a Plasma Actuator for a Small Unmanned Aerial Vehicle

et al. 2022

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The flow control capability (especially for separation control) of a dielectric-barrier-discharge plasma actuator (DBD-PA) has been investigated extensively. However, these studies have been conducted under ideal conditions, such as wind tunnels and computational environments, and limited studies have investigated the effects of plasma actuators in an actual environment. In this study, the flow control capability of a DBD-PA under natural and in-flight conditions was investigated via field flight tests using an unmanned aerial vehicle (UAV). The DBD-PA driving system was constructed with a small high-voltage power supply on a 2-m-span UAV. With the support of an autonomous flight system, the pitch angle gradually increased as the airspeed decreased, and the stall occurred from the cruise state. This flight procedure was conducted with the DBD-PA on or off, and 246 pairs of flights were operated. The results revealed that a flight state with a higher pitch angle and lower airspeed occurred when DBD-PA was switched on. In addition, the moment of stall was quantitatively determined from the flight log, and it was confirmed that the maximum pitch angle when DBD-PA was switched on tended to be larger than that when DBD-PA was switched off. These results indicate that flow control with a DBD-PA on a 2-m-span UAV was effective in natural and in-flight situations.

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Section: Introductionmentioning

confidence: 43%

In-Flight Demonstration of Stall Improvement Using a Plasma Actuator for a Small Unmanned Aerial Vehicle

et al. 2022

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“…The high voltage waveform has a great effect on the control authority of the DBD plasma actuator. In reference [13], nanosecond pulsed dielectric barrier discharge (DBD) actuators have been installed on a NACA 0015 airfoil and the operation of the actuator at the dominant experimentally measured flow frequencies at stall conditions was shown to give good control authority.…”

Section: Flow Control Applicationsmentioning

confidence: 99%

Special Issue “Active Flow Control Technologies for Energy and Propulsive Systems”

Giorgi

Ficarella

2019

Applied Sciences

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Vortex Breakdown Control by the Plasma Swirl Injector

Jiang

et al. 2021

Applied Sciences

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Vortex breakdown, observed in swirling flows, is an interesting physical phenomenon relevant to a wide range of engineering applications, including aerodynamics and combustion. The concept of using a plasma swirler to control vortex breakdown was proposed and tested in this study. The effect of plasma actuation on controlling the onset and development of the vortex breakdown was captured by particle image velocimetry. Flowfield measurement results suggested that, by varying the strength of the plasma actuation, the location and size of the vortex breakdown region was controlled effectively. The plasma swirl injector offers a method for optimal control and efficient utilization of vortex breakdown. The method being proposed here may represent an attractive way of controlling vortex breakdown using a small amount of energy input, without a moving or intrusive part.

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Mechanisms of Control Authority by Nanosecond Pulsed Dielectric Barrier Discharge Actuators on Flow Separation

Cited by 4 publications

References 21 publications

In-Flight Demonstration of Stall Improvement Using a Plasma Actuator for a Small Unmanned Aerial Vehicle

In-Flight Demonstration of Stall Improvement Using a Plasma Actuator for a Small Unmanned Aerial Vehicle

Special Issue “Active Flow Control Technologies for Energy and Propulsive Systems”

Vortex Breakdown Control by the Plasma Swirl Injector

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