Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

Little, Jesse; Takashima, Keisuke; Nishihara, Munetake; Adamovich, Igor V.; Samimy, Mo

doi:10.2514/1.j051114

Cited by 294 publications

(200 citation statements)

References 36 publications

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“…If the discharge power is not su©ciently large to e¨ectively excite the shear layer, only the ¦rst mechanism remains [15, 19 23]. These shedding structures have been observed also in particle image velocimetry (PIV) measurements for relatively low-speed §ow (up to 60 m/s) in a study by Little et al [19].…”

Section: Introductionmentioning

confidence: 90%

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Investigation of flow separation control by nanosecond pulsed dielectric barrier discharge actuators

Grech

Leyland

Peschke

et al. 2015

Progress in Flight Physics – Volume 7

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The ability of nanosecond pulsed dielectric barrier discharge (DBD) actuators to control §ow separation was investigated on a NACA (National Advisory Committee for Aeronautics) 0015 pro¦le for velocities up to 24 m/s (Re = 230,000). The optimal location for the actuator was determined from oil §ow experiments. Moderate voltage levels were applied (3 and 6 kV) and the actuator was operated at frequencies ranging from 0.058 to 10 kHz in pulse and burst modes. The peak e¨ectiveness of the actuator occurred at reduced frequency values of around 1. Plasma in §uence was observed at all tested angles of attack (up to 26 • ) and the stall angle was delayed by 8 • .

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Section: Introductionmentioning

confidence: 90%

“…A preference for low-frequency actuation is generally seen, with maximum §ow attachment obtained in the range of F + c = 1 to 2 for a NACA 0015 airfoil [7,19]. As the value of F + c is increased, the in §uence of the plasma on the §ow attachment weakens.…”

Section: Introductionmentioning

confidence: 91%

Investigation of flow separation control by nanosecond pulsed dielectric barrier discharge actuators

Grech

Leyland

Peschke

et al. 2015

Progress in Flight Physics – Volume 7

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“…First, the capability of ns-DBD plasma actuators for controlling leading edge separation on a NACA 0012 is confirmed. This AFC technique has been used with great success for NASA EET (Little et al 2012) and NACA 0015 (Rethmel et al 2011) airfoils in the past and it is not surprising that it is also successful here. Second, the capability of ns-DBDs for exciting coherent vortical wakes is evaluated in detail.…”

Section: Introductionmentioning

confidence: 87%

“…The unsteadiness generation technique is based on the use of ns-DBD plasma actuators for boundary layer separation control. In previous efforts, ns-DBD plasma was used as a flow control actuator for delaying static airfoil stall (Roupassov et al 2009, Rethmel et al 2011, Little et al 2012, Kelley 2014. It was also observed that the ns-DBD could initiate vortex formation in the airfoil wake over a substantial bandwidth up to Re and Mach (M) numbers of 1.15 x 10 6 and 0.26 respectively (Rethmel et al 2011).…”

Section: Introductionmentioning

confidence: 99%

“…Example mean velocity profiles for ns and ac-DBD plasma actuators operating in quiescent air with 2 kHz carrier frequency using (a) 100% and (b) 50% duty cycle at 90 Hz measured 20 mm downstream on a 30 cm DBD load . Phase-averaged schlieren images of compression waves generated by a nanosecond pulse discharge for several time delays after the discharge pulse (Little et al 2012). Images taken along the axis of the discharge.…”

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confidence: 99%

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Control of Boundary Layer Separation and the Wake of an Airfoil using ns-DBD Plasma Actuators

Ashcraft

2016

54th AIAA Aerospace Sciences Meeting

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Characterization of the single nanosecond pulsed surface dielectric barrier plasma actuator: Geometric and electric effects

Cai

Wang

et al. 2020

Contributions to Plasma Physics

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The influence of the electrode length and the voltage pulses on the discharge characteristics of the surface dielectric barrier discharge actuators were investigated numerically by using the plasma kinetic model. The governing equations including the coupled continuity plasma discharge equation, drift‐diffusion equation, electron energy equation, Poisson's equation, and Navier–Stokes equation were solved in quiescent air at atmospheric pressure. The results show that the shorter pulse rising time results in higher discharge characteristics, more intense discharge, and bigger discharge region. Differently, the compared discharge characteristics for the electrodes with different lengths prove that the length of the powered and ground electrodes has little effect on the surface dielectric barrier discharge driven by nanosecond pulsed voltage.

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Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

Cited by 294 publications

References 36 publications

Investigation of flow separation control by nanosecond pulsed dielectric barrier discharge actuators

Investigation of flow separation control by nanosecond pulsed dielectric barrier discharge actuators

Control of Boundary Layer Separation and the Wake of an Airfoil using ns-DBD Plasma Actuators

Characterization of the single nanosecond pulsed surface dielectric barrier plasma actuator: Geometric and electric effects

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