The multichannel discharge plasma synthetic jet actuator

Zhang, Zhibo; Wu, Yun; Jia, Ming; Song, Huimin; Sun, Zhengzhong; Zong, Haohua; Li, Yinghong

doi:10.1016/j.sna.2016.11.011

Cited by 37 publications

(15 citation statements)

References 25 publications

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“…As a consequence, there exists a significant time delay (30 µs) between the breakdown of the first and the last gap. This differs largely from the discharge reported in Zhang et al (2017), where a time delay of less than 1 µs is recorded. During the discharge, the arc voltage remains approximately at 300 V and experiences considerable electromagnetic interference during the ignition and quench phase.…”

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confidence: 99%

“…The preliminary scheme of one power supply per actuator adopted initially in laboratory tests is not feasible in practice due to the assosciated complexity and weight penalty (Narayanaswamy, Raja & Clemens 2012). Zhang et al (2017) proposed a sequential breakdown scheme and demonstrated simultaneous operation of up to 13 actuators with one power supply system. However, under this concept, the extension of the array by one actuator is accompanied by the addition of an extra resistor and a high-voltage capacitor to the power supply system, resulting in a complex structure and considerable space and weight penalty.…”

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confidence: 99%

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Realisation of plasma synthetic jet array with a novel sequential discharge

Zong

Kotsonis

2017

Sensors and Actuators A: Physical

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The Plasma Synthetic Jet Actuator (PSJA) is a zero-net mass flow actuator, capable of producing supersonic pulsed jets at high frequency (>5kHz). Successful application of PSJA to active flow control necessitates the removal of two obstacles, namely, low energy conversion efficiency and small jet affected length. A novel sequential discharge scheme employing a simple architecture is proposed to feed a PSJA array of multiple actuators. Phase-locked Particle Imaging Velocimetry (PIV) and electrical measurements are exploited to quantify the performance of the PSJA array. The jet impulse and jet mechanical energy of the PSJA array first improves and then drops, when the actuator number ranges from 1 to 6. Compared to that of single actuator, the discharge efficiency of PSJA array at an actuator number of 4 is increased by 10%, and the electro-mechanical energy is augmented by 340%. Additionally, the jet affected length is extended from the order of 10 mm to the order 100 mm.

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confidence: 99%

Realisation of plasma synthetic jet array with a novel sequential discharge

Zong

Kotsonis

2017

Sensors and Actuators A: Physical

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“…The discharge circuits proposed by Zhang et al (2017a) and Zong and Kotsonis (2017c) are combined to power the actuator array in this study. Figure 2 shows the power supply system.…”

Section: Discharge Scheme and Power Supply Systemmentioning

confidence: 99%

Airfoil flow separation control with plasma synthetic jets at moderate Reynolds number

2018

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An array of 26 plasma synthetic jet actuators (PSJA) is flush-mounted on a NACA-0015 airfoil model to control the leadingedge flow separation at moderate Reynolds number (Re c = 1.7 × 10 5). The stall angle of this airfoil is postponed from 15.5 • to approximately 22 • , and the peak lift coefficient is increased by 21%. PSJAs exhibit distinctive separation control mechanisms depending on the relative location between actuation and separation and reduced frequency of actuation (F *). At an angle of attack of = 15.5 • , the non-actuated flow separates approximately 4% chord length downstream of the jet orifices. Plasma synthetic jets (PSJs) applied at F * ≥ 0.5 can displace the separation point downstream to mid-chord position, as a result of the energizing of the incoming boundary layer through mixing enhancement. As a comparison, with actuation frequency of F * ≤ 0.25 , the separation point at = 15.5 • remains near the leading edge and the zero-velocity line is periodically swept towards the suction surface by the convecting spanwise vortices generated from PSJ actuation, leading to a reduction of timeaveraged backflow area. For the case of separation control at = 22 • , the separation point resides always upstream of the actuation position, regardless of actuation frequency. The peak lift coefficient is attained at F * = 1 , and the decreasing lift at high actuation frequency (F * = 2) is ascribed to the severe interaction between adjacent spanwise vortices at short spacing.

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“…Among the existing plasma aerodynamic excitation methods, dielectric barrier discharge plasma excitation has a small intensity and weak flow control effect, which is unsuitable for high‐speed flow control. [ 22,23 ] Furthermore, both the intensity of the pulsed microwave excitation and power consumption are large, and it is difficult to arrange multiple sets of excitations. [ 24 ] The plasma synthetic jet excitation can only drive 1–3 sets of excitations at the same time; hence, the flow control effect is weak.…”

Section: Introductionmentioning

confidence: 99%

Experimental study on high‐energy surface arc plasma excitation control of cylindrical detached shock wave

Tang

Guo

Liang

2020

Contributions to Plasma Physics

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In this study, an electrical parameter test system and a high-speed Schlieren system are used to study the control of a cylindrical detached shock wave through high-energy surface arc plasma excitation. The results show that, when plasma excitation is not applied, the bow shockwave angle around the cylinder is 52 •. After the plasma excitation is applied, the arc discharge releases a large amount of heat within a short time, generating a shockwave and a control gas bulb (CGB). As a result, the bow shockwave angle first decreases and then increases, the pressure ratio before and after the shockwave decreases, and the intensity of the bow shockwave weakens. At t = 280 μs, the bow shockwave angle is reduced to a minimum of 46 •. The effective interference time of high-energy surface arc plasma excitation on a cylindrical detached shockwave is 820 μs. A high temperature is used to control the heating effect of the bubbles, which will increase the local sound velocity near the wall, reduce the local Mach number, cause the sound velocity to move online, and eventually push the bow shockwave away from the cylinder. Concurrently, heating will accelerate the gas flow, reduce the pressure, and cause the mass flow in the unit flow area of the heated area to decrease, resulting in a strong compression effect, which deforms the bow shockwave. The high-energy surface arc plasma excitation will provide a potential technical means for high-speed aircraft detached shockwave control.

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The multichannel discharge plasma synthetic jet actuator

Cited by 37 publications

References 25 publications

Realisation of plasma synthetic jet array with a novel sequential discharge

Realisation of plasma synthetic jet array with a novel sequential discharge

Airfoil flow separation control with plasma synthetic jets at moderate Reynolds number

Experimental study on high‐energy surface arc plasma excitation control of cylindrical detached shock wave

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