Transient Flow Patterns of Multiple Plasma Synthetic Jets Under Different Ambient Pressures

Zhang, Yuchao; Tan, Huijun; Huang, He-xia; Sun, Shu Wen; He, Xiaoming; Cheng, Lin; Zhuang, Yi

doi:10.1007/s10494-018-9931-5

Cited by 13 publications

(3 citation statements)

References 17 publications

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“…Under such a background, active flow control (AFC) for suppressing airfoil stall has been attached much importance and developed rapidly. So far, the novel periodic excitation method by using synthetic jet is demonstrated to be one of the most promising AFC methods on controlling stall characteristics of an airfoil [13][14][15][16][17] .…”

Section: Openmentioning

confidence: 99%

Wind-tunnel tests of synthetic jet control effects on airfoil flow separation

Zhao

Chen

2022

Sci Rep

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To find out the comprehensive principles of synthetic jet control effects on airfoil stall characteristics, fundamental contrastive wind-tunnel tests were conducted systematically. By using six-component balance, Particle Image Velocimetry (PIV) technology and boundary layer probe, the measurements of model aerodynamic forces, the whole velocity field over airfoil and velocity profiles in the boundary layer were conducted, respectively. Based upon the experimentally parametric analyses of synthetic jet control on airfoil, it is concluded that the incline angle of synthetic jet has an important impact on both the flow in boundary layer and aerodynamic forces of airfoil. A tangential jet inject energy and accelerate the velocity of flow in inner boundary layer thus has a better control effects on delay stall of airfoil when the momentum coefficient of jet is relatively large, and the normal jet helps to enlarge the thickness of boundary layer which is proved to have better control effects on flow separation control and improving the aerodynamic characteristics of airfoil when the momentum coefficient of a jet is relatively small.

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Section: Openmentioning

confidence: 99%

Wind-tunnel tests of synthetic jet control effects on airfoil flow separation

Zhao

Chen

2022

Sci Rep

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“…As the flight speed range increases, it is difficult to coordinate the low-speed starting performance and the high-speed cruising performance of the ramjet, which seriously restricts the engine performance improvement [1]. In order to improve the inlet performance, many studies have been carried out on various active and passive flow control methods, such as boundary layer suction [2,3], plasma [4][5][6], vortex generators [7][8][9][10], and so on. These flow control methods could improve the shock wave/boundary layer interference and other flow field characteristics, and improve the inlet performance to a certain extent.…”

Section: Introductionmentioning

confidence: 99%

Study on a Two-Dimensional Supersonic Inlet with Inner Profile Adjustment

et al. 2022

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According to the requirements of a wide speed range, a variable-geometry supersonic inlet with inner surface adjustment is studied. The basic design model of the inlet is established, and the influence of profile adjustment on the resisting back pressure ability and inlet performance boundary are analyzed using a theoretical method. Based on the numerical simulation method, the flow field simulation is carried out, and the flow field parameter distribution and performance of the adjustment inlet are studied in comparison with the fixed-geometry scheme. The results show that the starting Mach number is not changed for two inlet schemes because they have the same profile during low-speed flight. The fixed-geometry inlet has insufficient compression on the incoming flow, and the resisting back pressure ability decreases significantly during high-speed flight. The compression ratio and the compression wave system can be easily changed at the same time through the adjustment of the inner profile for the adjustable inlet during high-speed flight. Both the theoretical analysis and numerical simulation show that the resisting back pressure ability and performance are significantly improved after the adjustment. As such, the adjustment method in this paper can fundamentally solve the problem of the insufficient compression of the wide-range working inlet during high-speed flight, and the method can be easily realized.

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“…The SPJ actuator has been a hot research topic in plasma flow control field for the past 17 years [13][14][15][16][17][18]. On the one hand, the researchers conducted a detailed parametric study of SPJ actuator [19][20][21][22][23]. On the other hand, a large number of studies focused on the working characteristic [24][25][26], efficiency improvement [27,28] and structure optimization [29][30][31] of SPJ actuator.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study on Ramp Shock Wave Control in Ma3 Supersonic Flow Using Two-Electrode SparkJet Actuator

et al. 2020

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The control of a shock wave produced by a ramp (ramp shock) in Ma3 supersonic flow using a two-electrode SparkJet (SPJ) actuator in a single-pulse mode is studied experimentally. Except for schlieren images of the interaction process of SPJ with the flow field, a dynamic pressure measurement method is also used in the analysis of shock wave control. In a typical experimental case, under the control of single-pulsed SPJ, the characteristic of ramp shock changes from “short-term local upstream motion” in the initial stage to “long-term whole downstream motion” in the later stage. The angle and position of the ramp shock changes significantly in the whole control process. In addition, the dynamic pressure measurement result shows that the ramp pressure is reduced by a maximum of 79% compared to that in the base flow field, which indicates that the ramp shock is significantly weakened by SPJ. The effects of some parameters on the control effect of SPJ on the ramp shock are investigated and analyzed in detail. The increase in discharge capacitance helps to improve the control effect of SPJ on the ramp shock. However, the control effect of the SPJ actuator with medium exit diameter is better than that with a too small or too large one. In addition, when the SPJ exit is located in the separation zone and outside, the change in the ramp shock shows significant differences, but the control effect in the case of medium ramp distance is better when the SPJ exit is located outside the separation zone.

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Transient Flow Patterns of Multiple Plasma Synthetic Jets Under Different Ambient Pressures

Cited by 13 publications

References 17 publications

Wind-tunnel tests of synthetic jet control effects on airfoil flow separation

Wind-tunnel tests of synthetic jet control effects on airfoil flow separation

Study on a Two-Dimensional Supersonic Inlet with Inner Profile Adjustment

Experimental Study on Ramp Shock Wave Control in Ma3 Supersonic Flow Using Two-Electrode SparkJet Actuator

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