Effects of plasma aerodynamic actuation on oblique shock wave in a cold supersonic flow

Wang, Jian; Li, Yinghong; Cheng, Baolei; Changbing, Su; Song, Huimin; Wu, Yun

doi:10.1088/0022-3727/42/16/165503

Cited by 33 publications

(14 citation statements)

References 13 publications

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“…The other mechanism is the generation of streamwise vortices caused by the pulsed arc discharges, which leads to a fuller boundary layer profile, making it less resistant to separation. Wang et al 15 employed a pulsed-arc discharge in the presence of an external magnetic field to weaken the separation shock generated by a 20 • compression ramp placed in a Mach 2.1 flow. The authors reported an increase in the weakening of the shock strength with external magnetic field.…”

Section: Introductionmentioning

confidence: 99%

Control of unsteadiness of a shock wave/turbulent boundary layer interaction by using a pulsed-plasma-jet actuator

Narayanaswamy¹,

Raja²,

Clemens³

2012

Physics of Fluids

166

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A pulsed-plasma jet actuator is used to control the unsteady motion of the separation shock of a shock wave/boundary layer interaction formed by a compression ramp in a Mach 3 flow. The actuator is based on a plasma-generated synthetic jet and is configured as an array of three jets that can be injected normal to the cross-flow, pitched, or pitched and skewed. The typical peak jet exit velocity of the actuators is about 300 m/s and the pulsing frequencies are a few kilohertz. A study of the interaction between the pulsed-plasma jets and the shock/boundary layer interaction was performed in a time-resolved manner using 10 kHz schlieren imaging. When the actuator, pulsed at St L ≈ 0.04 (f = 2 kHz), was injected into the upstream boundary layer, the separation shock responded to the plasma jet by executing a rapid upstream motion followed by a gradual downstream recovery motion. Schlieren movies of the interaction showed that the separation shock unsteadiness was locked to the pulsing frequency of the actuator, with amplitude of about one boundary layer thickness. Wall-pressure measurements made under the intermittent region showed about a 30% decrease in the overall magnitude of the pressure fluctuations in the low-frequency band associated with unsteady large-scale motion of the separated flow. Furthermore, by increasing the pulsing frequency to 3.3 kHz, the amplitude of the separation shock oscillation was reduced to less than half the boundary layer thickness. Investigation into the effect of the actuator location on the shock wave/boundary layer interaction (SWBLI) showed qualitatively and quantitatively that the actuator placed upstream of the separation shock caused significant modification to the SWBLI unsteadiness, whereas injection from inside the separation bubble did not cause a noticeable effect.

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Section: Introductionmentioning

confidence: 99%

Control of unsteadiness of a shock wave/turbulent boundary layer interaction by using a pulsed-plasma-jet actuator

Narayanaswamy¹,

Raja²,

Clemens³

2012

Physics of Fluids

166

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“…直流放电等离子体较强的加热效应, 可以产生较高的等离子体密度. 当施加合适的外部磁场时, 通过磁流体动力的约束作用 , 可以降低放电功率需求 [132] , 同时提高等离子体控制效果 [133] . 火花放电等离子体激励器的工作特性受能量沉积大小、激励器腔体和出口大小的影响 [136,137] , 另外 Belinger 等人 [138] 还实验研究了电能的释放速率对激励器工作特性的影响.…”

Section: 脉冲射流激励器unclassified

高速流场主动流动控制激励器研究进展

夏¹,

刘²,

王³

et al. 2012

Sci. Sin.-Tech.

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“…Yan [8] promoted the supersonic boundary layer transition using the so-called 'thermal bump' (∆Tw=500K, f=100 kHz) through vortical structures. Falempin and Wang [9][10] investigated the control authority of the steady DCD (2-10 kW and 1-1.5 kW) on shock wave modification. It was found that the resulted thermal choking could weaken the shock wave strength and reduce the shock drag.…”

Section: Introductionmentioning

confidence: 99%

Characterization of transverse plasma jet and its effects on ramp induced separation

Tang

Wang

et al. 2018

Experimental Thermal and Fluid Science

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Plasma synthetic jet actuator (PSJA), which produces pulsed jets, is used to control the shock wave boundary layer interaction at a compression ramp at Ma=2.0. The flow topology of the wall jets from the PSJA is first visualised through particle laser scattering (PLS) photography. The PSJA aperture effect is also examined by comparing the jets out of the apertures of 1,2 mm and 2 mm respectively. The control effect is later investigated by both PLS and particle image velocimetry (PIV). , which was erupted from different jet apertures of 1.2mm and 2mm, were compared experimentally in a wind tunnel of Mach 2. Further, the interaction between the TPJ and the ramp induced separation was explored. The phase-locked two-component particle image velocimetry (PIV) and particle laser scattering (PLS) were used for flow visualizations. The K-H vortices and hairpin vortices due to the shear stress between the jet plume and high-speed mainstream were identified.The results show that the TPJ in supersonic flow is characterized by two typical parts: the attached jet plume (AJP) and the detached jet plume (DJP). The penetration height of the jet plume, which is closely related to the jet aperture, plays a dominant role in the proportion of the two parts. The higher jet penetration height leads to the more detached jet plume. As for the interaction between the jet plume and separation zone, the attached jet plume was blocked by the separation zone, which formed a recirculation zone and contributed to an expansion of the separation. In contrast, the detached jet plume transited along the shear layer and then enhanced the velocity exchange between the shear layer and mainstream. Ultimately, the reduction of the separation zone was revealed with the overall shear layer reduced. Furthermore, a conceptual model based on two typical morphological features was suggested to reveal the interaction mechanism.

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Effects of plasma aerodynamic actuation on oblique shock wave in a cold supersonic flow

Cited by 33 publications

References 13 publications

Control of unsteadiness of a shock wave/turbulent boundary layer interaction by using a pulsed-plasma-jet actuator

Control of unsteadiness of a shock wave/turbulent boundary layer interaction by using a pulsed-plasma-jet actuator

高速流场主动流动控制激励器研究进展

Characterization of transverse plasma jet and its effects on ramp induced separation

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