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Experimental study on shock interaction control of double wedge in high-enthalpy hypersonic flow subject to plasma synthetic jet

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Chinese Journal of Aeronautics 2024年第4期37卷 151-165页

作者： Xuzhen XIE Qiang LIU Yan ZHOU Zhenbing LUO Wei XIE Guanghui BAI Kai LUO Qiu WANG Jianjun WU College of Aerospace Science and Engineering National University of Defense TechnologyChangsha 410073China China Academy of Launch Vehicle Technology Beijing 100076China Institute of Mechanics Chinese Academy of SciencesBeijing 100190China

The hypersonic shock-shock interaction flow field at double-wedge geometries controlled by plasma synthetic jet actuator is experimentally studied in a Ma = 8 high-enthalpy shock tunnel with the purpose of exploring a novel technique for reducing surface heat flux in a real flight environment. The results demonstrate that increasing the discharge energy is advantageous in eliminating the shock wave, shifting the shock wave interaction point, and shortening the control response time. The oblique shock wave can be completely removed when the actuator's discharge energy grows from 0.4 J to 11.5 J, and the displacement of the shock wave interaction point increases by 124.56%, while the controlled response time is shortened by 30 μs. Besides, the reduction in diameter of the jet exit is firstly proved to have a negative impact on energy deposition in a working environment with incoming flow, which reduces the discharge energy and hence decreases the control effect. The shock wave control response time lengthens when the jet exits away from the second wedge. Along with comparing the change in wall heat flux at the second wedge over time, the control effect of plasma synthetic jet actuator with and without inflation is also analyzed. When plasma synthetic jet works in inflatable mode, both the ability to eliminate shock waves and the shifting effect of the shock wave interaction point are increased significantly, and the wall heat flux is also reduced.

关键词： Hypersonic flow High-enthalpy flow plasma synthetic jet Shock wave Flow control

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Effect of three-electrode plasma synthetic jet actuator on shock wave control

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Science China(Technological Sciences) 2017年第1期60卷 146-152页

作者： ZHOU Yan XIA ZhiXun LUO ZhenBing WANG Lin Science and Technology on Scramjet Laboratory National University of Defense Technology Changsha 410073 China

A three-electrode high-energy plasma synthetic jet(PSJ) actuator was used for shock wave control. This actuator is an enhanced version of the two-electrode actuator as a high-voltage trigger electrode is added to increase the cavity volume and the input energy while retaining a relatively low disruptive voltage. The electrical properties were studied using current-voltage measurements, and the energy consumption was calculated. To assess the jet strength, the penetration of PSJ was compared with empirical values, and the results show that the momentum flux ratio of PSJ for a capacitance of 0.96, 1.6, and 3 μF was approximately equal to 0.6, 1.0, and 1.3, respectively. The interaction of PSJ with shock waves was acquired using high-speed shadowgraph imaging. The shock was generated by a 25° compression ramp in Mach 2 flow, and PSJ actuator was placed up-stream of the compression ramp. Under the action of PSJ, the strength of the shock was notably weakened, and the near-wall part of the shock was entirely eliminated. The results show the good control effect of the three-electrode high-energy PSJ in high-speed flow.

关键词： plasma synthetic jet three-electrode shock wave active flow control

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Parametric study of high-frequency characteristics of plasma synthetic jet actuator

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plasma Science and Technology 2021年第12期23卷 140-149页

作者： Guozheng SONG Haohua ZONG Hua LIANG Zhi SU Like XIE Xing ZHENG Science and Technology on plasma Dynamics Laboratory Air Force Engineering UniversityXi'an 710038People's Republic of China School of Mechanical Engineering Xi'an Jiaotong UniversityXi'an 710049People's Republic of China

A major issue of plasma synthetic jet actuator(PSJA)is the severe performance deterioration at high working *** this study,experiments and numerical simulation are combined together to investigate the influence of thermal conductivity,throat length(Lth)and discharge duration(Td)on the high-frequency characteristics of *** show that the variation of the actuator thermal conductivity and discharge duration will not alter the saturation frequency of the actuator,whereas decreasing the throat length results in an increase of the saturation *** a short-duration capacitive discharge of 1.7μs,a clear shock wave is issued from the orifice,followed by a weak *** a comparison,when the discharge duration is increased up to 202.6μs,a strong jet column is formed and no obvious shock wave can be *** on numerical simulation results,it becomes clear that the long-duration pulse-DC discharge is able to heat the cavity gas to a much higher temperature(3141 K)than capacitive discharge,greatly improving the conversion efficiency of the arc discharge energy to the internal energy of the cavity *** addition,high-speed Schlieren imaging is deployed to study the performance degradation mechanism of PSJA at high working *** of the exit jet grayscale indicates that as long as the saturation frequency is exceeded,the actuator becomes unstable due to insufficient refresh *** higher the discharge frequency,the more frequently the phenomenon of‘misfires’will occur,which explains well the decaying jet total pressure at above saturation frequency.

关键词： thermal conductivity throat length discharge duration plasma synthetic jet saturation frequency

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Experimental characteristics of a two-electrode plasma synthetic jet actuator array in serial

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Chinese Journal of Aeronautics 2018年第12期31卷 2234-2247页

作者： Yan ZHOU Zhixun XIA Zhenbing LUO Lin WANG Xiong DENG Science and Technology on Scramjet Laboratory National University of Defense Technology

plasma synthetic jet(PSJ) actuators have shown wide and promising application prospects in high-speed flow control, due to their advantages including high exhaust speed, wide frequency band, rapid response, and non-moving components. Although previous studies on PSJ actuators are abundant, most of them have focused on the performance of a single actuator. However, in practice, an actuator array is very necessary for large-scale aerodynamic actuation on account of the small affected area of a single PSJ. In this paper, the characteristics of a twoelectrode plasma synthetic jet actuator array in serial are investigated experimentally. Compared to a parallel actuator array, the serial actuator array requires simpler power supply design and is much easier to realize. High-speed photography of the discharge evolution, voltage-current measurement, and shadowgraphy visualization are used in the investigation. Experimental results show that, for the serial actuator array, weak discharges happen firstly between energized and suspending electrodes, and then a strong pulse arc discharge is triggered. The breakdown voltage in serial is irrelevant to such factors as the number of actuators, the maximum or minimum gap in serial,the connection sequence, etc. It is mainly determined by the sum of gaps. For serial actuators with the same anode-to-cathode spacing, the energy deposition is the same, and the jet is synchronous and similar. Because of the entrainment and merging of adjacent jet vortices, the jet front speed of an aligned synchronous jet array increases as the orifice distance decreases. To achieve the highest jet front velocity, the orifice of the actuator has an optimal diameter.

关键词： Capacitive power supply Flow control plasma synthetic jet Pulse arc discharge Serial actuator array Two-electrode

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Suppressing unsteady motion of shock wave by high-frequency plasma synthetic jet

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Chinese Journal of Aeronautics 2021年第9期34卷 60-71页

作者： Yanhao LUO Jun LI Hua LIANG Shanguang GUO Mengxiao TANG Hongyu WANG Science and Technology on plasma Dynamics Laboratory Air Force Engineering UniversityXi’an 710038China Hypervelocity Aerodynamics Institute China Aerodynamics Research and Development CenterMianyang 621000China

Three plasma synthetic jet Actuators(PSJA)under the high-frequency actuation are used to control the Shock Wave Boundary Layer Interaction(SWBLI),a high-speed schlieren image processing method based on spatial Fourier transform as well as snapshot proper orthogonal decomposition were used to study the control effect of high-frequency plasma synthetic jet on lowfrequency unsteadiness of *** analysis of the base flow shows that the separated shock wave actually has both large-and small-amplitude vibrations at low *** the results revealed that the PSJA with an operating frequency of 2 k Hz has the ability to reduce the energy of low-frequency component of shock wave motion,indicating that the 2 k Hz actuation can effectively suppress low-frequency unsteadiness of the separated *** with the actuation frequency of 2 k Hz,the energy of low-frequency component of the shock wave is enhanced under the8 k Hz actuation,which aggravates the low-frequency unsteady motion of the shock *** is likely that the actuation frequency is too high,thus the intensity of the precursor shock wave induced by PSJA becomes ***,as the 4 k Hz actuation is applied,the pulsation of the separation region was enhanced,it is speculated that the actuation frequency is coupled with the oscillation frequency of the separation region.

关键词： Flow control plasma synthetic jet Shock wave/boundary interaction Supersonic flow Unsteady motion

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Experimental study on airfoil flow separation control via an air-supplement plasma synthetic jet

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Advances in Aerodynamics 2022年第1期4卷 721-742页

作者： Ru-Bing Liu Wen-Tao Wei Hai-Peng Wan Qi Lin Fei Li Kun Tang School of Aerospace Engineering Xiamen UniversityXiamen361102China Fujian Provincial Key Laboratory of plasma and Magnetic Resonance Xiamen361005China Chengdu Aircraft Design and Research Institute Chengdu610041China Shanghai Aerospace Control Technology Institute Shanghai201100China Rotor Aerodynamics Key Laboratory China Aerodynamics Research and Development CenterMianyang621000China Science and Technology on plasma Dynamics Laboratory Air Force Engineering UniversityXi’an710038China

An air-supplement plasma synthetic jet(PSJ)actuator increases the air supplemental volume in the recovery stage and improves the jet energy by attaching a check valve to the chamber of a conventional *** explore the flow control effect and mechanism of the air-supplement actuator,via particle image velocimetry experiments in a low-speed wind tunnel,the flow field and boundary layer characteristics of a two-dimensional airfoil surface under different actuation states were compared for different attack angles and jet *** experimental results show that,compared with the conventional actuation state,the jet energy of the air-supplement PSJ is higher and the indirect mixing effect of the counter-vortex sequence produced by the jet-mainstream interaction is ***,the boundary layer mixing effect is better,which can further suppress flow separation and improve the critical flow separation attack ***,increasing the jet momentum coefficient can enhance the flow control *** findings of this study could provide guidance for the flow control application of air-supplement PSJs.

关键词： plasma synthetic jet Check valve Flow separation Active flow control Air-supplement

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Control of flow separation over a wing model with plasma synthetic jets

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plasma Science and Technology 2022年第6期24卷 135-147页

作者： Zhi SU Guozheng SONG Haohua ZONG Hua LIANG Jun LI Like XIE Xuecheng LIU Weiliang KONG Science and Technology on plasma Dynamics Laboratory Air Force Engineering UniversityXi'an 710038People's Republic of China Institute of Aero-Engine School of Mechanical EngineeringXi’an Jiaotong UniversityXi'an 710049People's Republic of China The Green Aerotechnics Research Institute of Chongqing Jiaotong University Chongqing 404100People's Republic of China

An array of 30 plasma synthetic jet actuators(PSJAs)is deployed using a modified multichannel discharge circuit to suppress the flow separation over a straight-wing *** lift and drag of the wing model are measured by a force balance,and the velocity fields over the suction surface are captured by a particle imaging velocimetry *** show that the flow separation of the straight wing originates from the middle of the model and expands towards the wingtips as the angle of attack *** flow separation can be suppressed effectively by the PSJAs *** best flow control effect is achieved at a dimensionless discharge frequency of F^+=1,with the peak lift coefficient increased by 10.5%and the stall angle postponed by 2°.To further optimize the power consumption of the PSJAs,the influence of the density of PSJAs on the flow control effect is investigated.A threshold of the density exits(with the spanwise spacing of PSJAs being 0.2 times of the chord length in the current research),below which the flow control effect starts to deteriorate *** addition,for comparison purposes,a dielectric barrier discharge(DBD)plasma actuator is installed at the same location of the *** the same power consumption,4.9%increase of the peak lift coefficient is achieved by DBD,while that achieved by PSJAs reaches 5.6%.

关键词： flow separation plasma synthetic jet density dielectric barrier discharge

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Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

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Science China(Technological Sciences) 2015年第11期58卷 1949-1955页

作者： LIU RuBing NIU ZhongGuo WANG MengMeng HAO Ming LIN Qi State Key Laboratory of Aerodynamics China Aerodynamics Research and Development Center School of Physics and Mechanical & Electrical Engineering Xiamen University Fujian Key Laboratory of plasma and Magnetic Resonance Aerodynamics Research Institute Aviation Industry Corporation of China

Spark discharge plasma synthetic jets(SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting balance at a 20 m/s wind speed. The aim was to explore the SPJ's effect on airfoil aerodynamic by examining SPJ generators' position along the chordwise and the jet flow direction about the chord. Near the wing leading edge, two SPJ generators raised the stall angle by 2° and increased the maximum lift coefficient by 9%. The drag coefficient was decreased by 33.1%, and the lift-drag ratio was increased by 104.2% at an angle of attack above 16°. The rolling-moment coefficient was modified by 0.002, and the yawing-moment coefficient was changed by 0.0007 at angles of attack in the range of 0°–16°. The results showed that SPJs can control wing aerodynamic forces at a high angle of attack and moments at a low angle of attack.

关键词： plasma synthetic jet spark discharge NACA 0021 airfoil aerodynamic performance aerodynamic control

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Effect of a transverse plasma jet on a shock wave induced by a ramp

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Chinese Journal of Aeronautics 2017年第6期30卷 1854-1876页

作者： Hongyu WANG Jun LI Di JIN Hui DAI Tian GAN Yun WU Aeronautics and Astronautics Engineering College Air Force Engineering University Xi'an 710038 China

We conducted experiments in a wind tunnel with Mach number 2 to explore the evolution of a transverse plasma jet and its modification effect on a shock wave induced by a ramp with an angle of 24°. The transverse plasma jet was created by arc discharge in a small cylindrical cavity with a 2 mm diameter orifice. Three group tests with different actuator arrangements in the spanwise or streamwise direction upstream from the ramp were respectively studied to compare their disturbances to the shock wave. As shown by a time-resolved schlieren system, an unsteady motion of the shock wave by actuation was found： the shock wave was significantly modified by the plasma jet with an upstream motion and a reduced angle. Compared to spanwise actuation, a more intensive impact was obtained with two or three streamwise actuators working together. From shock wave structures, the control effect of the plasma jet on the shock motion based on a thermal effect, a potential cause of shock modification, was discussed. Furthermore, we performed a numerical simulation by using the Improved Delayed Detached Eddy Simulation（IDDES） method to simulate the evolution of the transverse plasma jet plume produced by two streamwise actuators. The results show that flow structures are similar to those identified in schlieren images. Two streamwise vortices were recognized, which indicates that the higher jet plume is the result of the overlap of two streamwise jets.

关键词： Flow control Improved delayed detachededdy simulation (IDDES)method plasma synthetic jet Shock wave/boundary layerinteraction Time resolved schlierensystem

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