Volume 52 Issue 1
Mar.  2022
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Li Y H, Wu Y, Liang H, Zhu Y F, Zhang H D, Guo S G. Exploration and outlook of plasma-actuated gas dynamics. Advances in Mechanics, 2022, 52(1): 1-32 doi: 10.6052/1000-0992-21-044
Citation: Li Y H, Wu Y, Liang H, Zhu Y F, Zhang H D, Guo S G. Exploration and outlook of plasma-actuated gas dynamics. Advances in Mechanics, 2022, 52(1): 1-32 doi: 10.6052/1000-0992-21-044

Exploration and outlook of plasma-actuated gas dynamics

doi: 10.6052/1000-0992-21-044
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  • Corresponding author: yinghong_li@126.com
  • Received Date: 2021-09-13
  • Accepted Date: 2021-11-12
  • Available Online: 2021-11-13
  • Publish Date: 2022-03-21
  • Plasma-actuated gas dynamics is an inter-discipline that concerns both the force and flow characteristics of an object submerged in flow, and the internal flow characteristics under the interaction of plasma actuation and flow, thus standing in the frontier of aerodynamics, gas dynamics, and plasma dynamics. Plasma actuation is a controllable disturbance imposed on the flow by either the collective motion of charged particles under electro-magnetic force or the pressure, temperature, and property variation produced by gas discharge. Affected by the local unsteady plasma actuation, the status of gaseous flow will change remarkably, which leads to a potential improvement of the aerodynamic performance. There have been tremendous investigations on surface dielectric barrier discharge plasma actuation, plasma synthetic jet actuation, as well as their interactions with boundary layer flow, separate flow, and shock-dominated flow. A systematic review of these investigations leads to the conclusion that there exists a strong coupling effect between plasma actuation and the modulated flow, and plasma shock control is a key to improving the control authority. Future researches should be directed towards the development of highly efficient plasma actuation, excitation, and leverage of flow instabilities, revealing coupling mechanism, and improvement of control effect.

     

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  • [1]
    杜海. 2016. 纳秒脉冲介质阻挡放电等离子体激励器流动控制原理及应用研究. [博士论文]. 南京航空航天大学

    Du H. 2016. Research on principle and application of flow control of nanosecond pulse dielectric barrier discharge plasma actuator. [PhD Thesis]. Nanjing: Nanjing University of Aeronautics and Astronautics
    [2]
    洪延姬, 李倩, 王殿楷. 2016. 超声速飞行器的激光空气锥减阻方法. 北京: 科学出版社

    Hong Y J, Li Q, Wang Y K. 2016. Laser air cone drag reduction method for supersonic aircraft. Beijing: Science Press
    [3]
    李洋, 梁华, 贾敏, 宋慧敏, 李军, 魏彪. 2018. 等离子体合成射流改善翼型气动性能实验研究. 推进技术, 9: 28-34 (Li Y, Liang H, Jia M, Song H M, Li J, Wei B. 2018. Experimental research on improving airfoil aerodynamic performance by plasma synthetic jet. Journal of Propulsion Technology, 9: 28-34).
    [4]
    李应红, 吴云, 梁华, 等. 2010. 提高抑制流动分离能力的等离子体冲击流动控制原理. 科学通报, 55: 3060-3068 (Li Y H, Wu Y, Liang H, et al. 2010. The mechanism of plasma shock flow control for enhancing flow separation control capability. Chinese Science Bulletin (Chinese Ver), 55: 3060-3068).
    [5]
    李应红, 吴云. 2020. 等离子体激励调控流动与燃烧的研究进展与展望. 中国科学:技术科学, 50: 1252-1273 (Li Y H, Wu Y. 2020. Research progress and outlook of flow control and combustion control using plasma actuation. Science China Technological Sciences, 50: 1252-1273).
    [6]
    彭倩. 2018. 基于等离子体激励器控制湍流边界层减阻的参数优化研究. [硕士论文]. 深圳: 哈尔滨工业大学

    Peng Q. 2018. Parametric optimization of plasma actuators for drag reduction in a turbulent boundary layer. [Master Thesis]. Shenzhen: Harbin University of Technology
    [7]
    苏志, 李军, 梁华, 魏彪, 陈杰. 2018. 多路等离子体合成射流改善翼型性能实验研究. 推进技术, 9: 1928-1937 (Su Z, Li J, Liang H, Wei B, Chen J. 2018. Experimental research on the improvement of airfoil performance by multi-path plasma synthetic jet. Journal of Propulsion Technology, 9: 1928-1937).
    [8]
    吴云, 李应红, 朱俊强. 2007. 等离子体气动激励扩大低速轴流式压气机稳定性的实验. 航空动力学报, 22: 2025-2030 (Wu Y, Li Y H, Zhu J Q. 2007. Experiment on enlarging the stability of low-speed axial compressor by plasma aerodynamic actuation. Journal of Aerospace Power, 22: 2025-2030). doi: 10.3969/j.issn.1000-8055.2007.12.009
    [9]
    吴云, 李应红, 朱俊强. 2009. 等离子体气动激励抑制压气机叶栅角区流动分离的仿真与实验. 航空动力学报, 24: 830-835 (Wu Y, Li Y H, Zhu J Q. 2009. Simulation and experiment of plasma aerodynamic actuation to suppress the flow separation in the corner of compressor cascade. Journal of Aerospace Power, 24: 830-835).
    [10]
    吴云, 李应红. 2015. 等离子体流动控制研究进展与展望. 航空学报, 36: 381-405 (Wu Y, Li Y H. 2015. Progress and outlook of plasma flow control. Acta Aeronautica et Astronautica Sinica, 36: 381-405).
    [11]
    吴云, 张海灯, 于贤君, 等. 2017. 轴流压气机等离子体流动控制. 工程热物理学报, 38: 1396-1414 (Wu Y, Zhang H D, Yu X J, et al. 2017. Plasma flow control of axial compressor. Journal of Engineering Thermophysics, 38: 1396-1414).
    [12]
    张海灯, 李应红, 吴云, 等. 2014a. 高速压气机叶栅纳秒脉冲等离子体流动控制仿真研究. 航空学报, 35: 1560-1570 (Zhang H D, Li Y H, Wu Y, et al. 2014a. Simulation research on nanosecond pulsed plasma flow control of high-speed compressor cascade. Acta Aeronautica et Astronautica Sinica, 35: 1560-1570).
    [13]
    张海灯, 吴云, 贾敏, 等. 2014b. 压气机叶栅内流环境中纳秒脉冲等离子体的气动激励特性. 高电压技术, 40: 2140-2149 (Zhang H D, Wu Y, Jia M, et al. 2014b. Aerodynamic actuation characteristics of nanosecond pulsed plasma in the internal flow environment of compressor cascade. High Voltage Engineering, 40: 2140-2149).
    [14]
    张海灯, 吴云, 李应红, 等. 2014c. 叶栅等离子体流动控制布局优化和影响规律. 航空动力学报, 29: 2593-2605 (Zhang H D, Wu Y, Li Y H, et al. 2014c. Optimization and influence law of cascade plasma flow control layout. Journal of Aerospace Power, 29: 2593-2605).
    [15]
    张海灯, 吴云, 李应红, 汪一舟, 王长凯. 2020. 纳秒脉冲等离子体激励调控压气机叶型附面层流动探索研究. 工程热物理学报, 41: 2147-2153 (Zhang H D, Wu Y, Li Y H, Wang Y Z, Wang C K. 2020. Research on nanosecond pulsed plasma actuation to regulate the flow of compressor blade surface layer. Journal of Engineering Thermophysics, 41: 2147-2153).
    [16]
    张海灯, 吴云, 于贤君, 刘宝杰. 2019. 高负荷压气机失速及其等离子体流动控制. 工程热物理学报, 40: 289-299 (Zhang H D, Wu Y, Yu X J, Liu B J. 2019. High-load compressor stall and its plasma flow control. Journal of Engineering Thermophysics, 40: 289-299).
    [17]
    张鑫, 黄勇, 阳鹏宇. 2018. 等离子体无人机失速分离控制飞行实验. 航空学报, 39: 121587 (Zhang X, Huang Y, Yang P Y. 2018. Stall separation control using plasma of UAV flight experiment. Acta Aeronautica et Astronautica Sinica, 39: 121587).
    [18]
    赵光银, 李应红, 梁华, 化为卓, 韩孟虎. 2015. 纳秒脉冲表面介质阻挡等离子体激励唯象学仿真. 物理学报, 64: 015101 (Zhao G Y, Li Y H, Liang H, Hua W Z, Han M H. 2015. Phenomenological modeling of nanosecond pulsed surface dielectric barrier discharge plasma actuation for flow control. Acta. Phys. Sin-Ch. Ed., 64: 015101). doi: 10.7498/aps.64.015101
    [19]
    赵光银. 2015. 翼型/三角翼等离子体冲击流动控制机理研究. [博士论文]. 西安: 空军工程大学

    Zhao G Y. 2015. Research on the mechanism of airfoil/delta wing plasma flow control. [PhD Thesis]. Xi'an: Air Force Engineering University
    [20]
    赵勤, 吴云, 李应红, 等. 2013. 端壁等离子体气动激励抑制高负荷压气机叶栅角区流动分离实验. 航空动力学报, 28: 2129-2139 (Zhao Q, Wu Y, Li Y H, et al. 2013. Experimental study of end-wall plasma aerodynamic actuation to suppress flow separation in the corner region of a high-load compressor cascade. Journal of Aerospace Power, 28: 2129-2139).
    [21]
    赵小虎, 李应红, 岳太鹏. 2011. 等离子体气动激励抑制高负荷压气机叶栅流动分离的实验研究. 高电压技术, 37: 1521-1528 (Zhao X H, Li Y H, Yue T P. 2011. Experimental research on plasma aerodynamic actuation to suppress flow separation in high-load compressor cascade. High Voltage Engineering, 37: 1521-1528).
    [22]
    赵小虎, 吴云, 李应红, 等. 2012. 高负荷压气机叶栅分离结构及其等离子体流动控制. 航空学报, 33: 208-219 (Zhao X H, Wu Y, Li Y H, et al. 2012. Separation structure of high-load compressor cascade and its plasma flow control. Acta Aeronautica et Astronautica Sinica, 33: 208-219).
    [23]
    Adelgren R, Elliott G, Knight D, Zheltovodov A, Beutner A. 2001. Energy deposition in supersonic flows// 39th AIAA Aerospace Sciences Meeting and Exhibit, 2001-0885
    [24]
    Akcayoz E, Vo H D, Mahallati A. 2016. Controlling corner stall separation with plasma actuators in a compressor cascade. J. Turbomach., 138: 081008. doi: 10.1115/1.4032675
    [25]
    Alexandre V L, Mikhail N S, Dmitry F O, Richard B M and Sergey O M. 2010. Limitations of the DBD effects on the external flow// 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2010-470
    [26]
    Anderson K V, Knight D D. 2012. Plasma jet for flight control. AIAA J., 50: 1855-1872. doi: 10.2514/1.J051309
    [27]
    Ashrafi F, Michaud M, Vo H D. 2016. Delay of rotating stall in compressors using plasma actuators. J. Turbomach., 138: 091009. doi: 10.1115/1.4032840
    [28]
    Bedin A P, Mishin G I. 1995. Ballistic studies of the aerodynamics drag on a sphere in ionized air. Tech. Phys. Lett., 21: 5-7.
    [29]
    Belson B, Meidell K, Hanson R. 2012. Comparison of Plasma Actuators in Simulations and Experiments for Control of Bypass Transition// In: AIAA Aerospace Sciences Meeting Including the New Horizons Forum & Aerospace Exposition, 2012-1141
    [30]
    Bin W, Chao G, Feng L, Xue M, Wang Y and Zheng B. 2019. Reduction of turbulent boundary layer drag through DBD plasma actuation based on the Spalding formula. Plasma. Sci. Technol., 21: 045501. doi: 10.1088/2058-6272/aaf2e2
    [31]
    Caruana D, Rogier F, Dufour G, Gleyzes. 2013. The plasma synthetic jet actuator, physics, modeling and flow control application on separation. Aerospace Lab., 1-13.
    [32]
    Cheng X Q, Wong C W, Hussain F, W Schröder, Zhou Y. 2021. Flat plate drag reduction using plasma-generated streamwise vortices. J. Fluid. Mech., 918: A24. doi: 10.1017/jfm.2021.311
    [33]
    Chiatto M, de Luca L. 2017. Numerical and experimental frequency response of plasma synthetic jet actuators// 55th AIAA Aerospace Sciences Meeting, 2017-1884
    [34]
    Choi K S, Jukes T, Whalley R. 2011. Turbulent boundary-layer control with plasma actuators. Philos. T. R. Soc. A., 369: 1443-1458. doi: 10.1098/rsta.2010.0362
    [35]
    Correale G, Michelis T, Popov I. 2013. Disturbance introduced into a laminar Boundary Layer by a NS-DBD plasma actuator// AIAA Aerospace Sciences Meeting Including the New Horizons Forum & Aerospace Exposition, 2013-0752
    [36]
    Correale G, Michelis T, Ragni D, Kotsonis M, Scarano F. 2014. Nanosecond-pulsed plasma actuation in quiescent air and laminar boundary layer. J. Phys. D., 47: 264264.
    [37]
    Dong H, Geng X, Shi Z, Cheng K, Cui Y D, Khoo B C. 2019. On evolution of flow structures induced by nanosecond pulse discharge inside a plasma synthetic jet actuator. Jpn. J. Appl. Phys., 58: 028002. doi: 10.7567/1347-4065/aaf6e5
    [38]
    Du Y Q, Symeonidis V, George E K. 2002. Drag reduction in wall-bounded turbulence via a transverse travelling wave. J. Fluid. Mech., 457: 1-34. doi: 10.1017/S0022112001007613
    [39]
    Duchmann A, Grundmann S, Tropea C. 2012. Delay of natural transition with dielectric barrier discharges. Exp. Fluids, 54: 1461.
    [40]
    Duchmann A, Simon B, Magin P. 2013. In-flight transition delay with DBD plasma actuators// AIAA Aerospace Sciences Meeting, 2013-0900
    [41]
    Duong A H, Corke T C, Thomas F O. 2021. Characteristics of drag-reduced turbulent Boundary layers with pulsed-direct-current plasma actuation. J. Fluid. Mech., 915: A113. doi: 10.1017/jfm.2021.167
    [42]
    Elias P Q, Severac N, Luyssen M, Tobeli O, Lambert F, Bur R, Houard A. 2018. Experimental investigation of linear energy deposition using femtosecond laser filamentation in a M=3 supersonic flow// 54th AIAA/SEA/ASEE Joint Propulsion Conference, 2018-4896
    [43]
    Fang Y, Hong Q, Li H. 2011. Hypersonic wave drag reduction performance of cylinders with repetitive laser energy depositions. Journal of Physics Conference: Series, 276: 012021. doi: 10.1088/1742-6596/276/1/012021
    [44]
    Gaitonde D V. 2013. Analysis of plasma-based flow control mechanisms through large-eddy simulations. Comput. Fluids, 85: 19-26. doi: 10.1016/j.compfluid.2012.09.004
    [45]
    Gan T, Wu Y, Sun Z Z, Jin D. 2018. Shock wave boundary layer interaction controlled by surface arc plasma actuators. Phys. Fluids, 30: 055107. doi: 10.1063/1.5013166
    [46]
    Ganiev Y C, Gordeev V P, Krasilnikov A V, et al. 2000. Aerodynamic drag reduction by plasma and hot-gas injection. J. Thermophys. Heat Transfer, 14: 10-17. doi: 10.2514/2.6504
    [47]
    Greenblatt D, Kastantin Y, Nayeriet C N. 2007. Delta wing flow control using dielectric barrier discharge actuators. AIAA J., 46: 1554-1660.
    [48]
    Greene B R, Clemens N T, Magari T, Micka D. 2015. Control of mean separation in shock boundary layer interaction using pulsed plasma jets. Shock Waves, 25: 495-505. doi: 10.1007/s00193-014-0524-5
    [49]
    Grossman K, Bohdan C, van Wie D. 2003. Spark jet actuators for flow control// 41st Aerospace Sciences Meeting and Exhibit, 2003-53
    [50]
    Grundmann S, Frey M, Tropea C. 2009. Unmanned aerial vehicle (UAV) with plasma actuators for separation control// 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition, 2009-698
    [51]
    Grundmann S, Tropea C. 2007. Experimental transition delay using glow-discharge plasma actuators. Exp. Fluids, 42: 653-657. doi: 10.1007/s00348-007-0256-8
    [52]
    Grundmann S, Tropea C. 2008. Active cancellation of artificially introduced Tollmien–Schlichting waves using plasma actuators. Exp. Fluids, 44: 795-806. doi: 10.1007/s00348-007-0436-6
    [53]
    Haack S, Taylor T, Emhoff, Cybyk B. 2010. Development of an analytical spark jet model// 5th Flow Control Conference, 2010-4979
    [54]
    Han M H, Li J, Niu Z G, Liang H, Zhao G Y, Hua W Z. 2015. Aerodynamic performance enhancement of a flying wing using nanosecond pulsed DBD plasma actuator. Chin. J. Aeronaut., 28: 377-384. doi: 10.1016/j.cja.2015.02.006
    [55]
    Hanson R, Lavoie P, Bade K. 2012. Steady-state closed-loop control of bypass boundary layer transition using plasma actuators// AIAA Aerospace Sciences Meeting Including the New Horizons Forum & Aerospace Exposition, 012-1140
    [56]
    Hardy P, Barricau P, Caruana D, Gleyzes C, Belinger A, Cambronne P. 2010. Plasma synthetic jet for flow control// 40th Fluid Dynamics Conference and Exhibit, 2010-5103
    [57]
    Huang B, Zhang C, Adamovich I, Akishev Y, Shao T. 2020. Surface ionization wave propagation in the nanosecond pulsed surface dielectric barrier discharge: the influence of dielectric material and pulse repetition rate. Plasma Sources Sci. Technol., 29: 044001. doi: 10.1088/1361-6595/ab7854
    [58]
    Jothiprasad G, Murray R C, Essenhigh K. 2011. Control of tip-clearance flow in a low-speed axial compressor rotor with plasma actuation. J. Turbomach., 134: 021019.
    [59]
    Jukes T N, Choi K S, Johnson G A. 2016. Turbulent drag reduction by surface plasma through spanwise flow oscillation// 3rd AIAA Flow Control Conference, 2016-3693
    [60]
    Kaparos P, Koltsakidis S, Panagiotou P. 2018. Experimental investigation of DBD plasma actuators on a BWB aerial vehicle model// 2018 Flow Control Conference, 2018-4028
    [61]
    Keisuke T, Yvette Z, Walter R L, Igor V A. 2011. Characterization of a surface dielectric barrier discharge plasma sustained by repetitive nanosecond pulses. Plasma Sources Sci. T., 20: 055009. doi: 10.1088/0963-0252/20/5/055009
    [62]
    Kelley C L, Bowles P O, Cooney. 2014. Leading edge separation control using alternating-current and nanosecond pulse plasma actuator. AIAA J., 52: 1871-1884. doi: 10.2514/1.J052708
    [63]
    Khorunzhenko V, Roupassov D, Starikovskii A. 2002. Hypersonic flow and shock wave structure control by low temperature nonequilibrium plasma of gas discharge// 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2002-3569
    [64]
    Kim H, Ahn S, Kim K H. 2018. Numerical analysis on jet formation process of spark jet actuator// 2018 AIAA Aerospace Sciences Meeting, 2018-1552
    [65]
    Klimov A I, Koblov A N, Mishin G I, et al. 1982. Shock wave propagation in a glow discharge. Tech. Phys. Lett., 8: 192-194.
    [66]
    Kolesnichenko Y F, Azarova O A, Brovkin V G. 2004. Basics in beamed MW energy deposition for flow/flight control// 42nd AIAA Aerospace Sciences Meeting and Exhibit, 2004-0669
    [67]
    Laurendeau F, Chedevergne F, Casalis G. 2014. Transient ejection phase modeling of a plasma synthetic jet actuator. Phys. Fluids, 26: 125101. doi: 10.1063/1.4902394
    [68]
    Leonov S B, Yarantsev D A. 2008. Near-surface electrical discharge in supersonic airflow: properties and flow control. J. Propul. Power, 24: 1168-1181. doi: 10.2514/1.24585
    [69]
    Leonov S, Opaits D, Miles R, Soloviev V. 2010. Time-resolved measurements of plasma-induced momentum in air and nitrogen under dielectric barrier discharge actuation. Phys. Plasmas., 17: 113505. doi: 10.1063/1.3494279
    [70]
    Li C, Zhang Y, Lee C. 2020. Influence of glow discharge on evolution of disturbance in a hypersonic boundary layer: The effect of first mode. Phys. Fluids, 32: 051701. doi: 10.1063/5.0008457
    [71]
    Li Y H, Wu Y, Zhou M. 2010. Control of the corner separation in a compressor cascade by steady and unsteady plasma aerodynamic actuation. Exp. Fluids, 48: 1015-1023. doi: 10.1007/s00348-009-0787-2
    [72]
    Li Z, Shi Z W, Du H. 2018. Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing. Plasma Sci. Technol., 20: 115504. doi: 10.1088/2058-6272/aacaf0
    [73]
    Liu R, Niu Z, Wang M, Hao M, Lin Q. 2018. Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets. Sci. China Technol. Sci., 58: 1949-1955.
    [74]
    Meyer R, Palm P, Plonjes E, Rich W, Adamovich I V. 2003. The effect of a nonequilibrium RF discharge plasma on a conical shock wave in a M=2.5 flow. AIAA J, 41: 465-469.
    [75]
    Miles R B, Macheret S O, Martinelli L, Murray R, Shneider M, Yu Z. 2001. Plasma control of shock waves in aerodynamics and sonic boom mitigation// 32nd AIAA Plasma Dynamics and Lasers Conference and 4th Weakly Ionized Gases Workshop, 2001-3062
    [76]
    Narayanaswamy V, Raja L L, Clemens N T. 2010. Characterization of a high-frequency pulsed-plasma jet actuator for supersonic flow control. AIAA J., 48: 297-305. doi: 10.2514/1.41352
    [77]
    Narayanaswamy V, Raja L L, Clemens N T. 2012a. Control of a shock/boundary-layer interaction by using a pulsed-plasma jet actuator. AIAA J., 50: 246-249. doi: 10.2514/1.J051246
    [78]
    Narayanaswamy V, Raja L L, Clemens N T. 2012b. Control of unsteadiness of a shock wave/turbulent boundary layer interaction by using a pulsed-plasma-jet actuator. Phys. Fluids, 24: 076101. doi: 10.1063/1.4731292
    [79]
    Nishihara M, Takashima K, Rich W, Adamovich L V. 2011. Mach 5 bow shock control by a nanosecond pulse surface DBD// 49th Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011-1144
    [80]
    Opaits D F, Roupassov D V, Starikovskaia S M. 2004. Shock wave interaction with non-equilibrium plasma of gas discharge// 42nd AIAA Aerospace Sciences Meeting and Exhibit, 2004-1023
    [81]
    Patel M P, Ng T T, Vasudevan S. 2007. Plasma actuators for hingeless aerodynamic control of an unmanned air vehicle. J. Aircr., 44: 1264-1274. doi: 10.2514/1.25368
    [82]
    Peter P, Rodney M. 2003. Nonequilibrium radio frequency discharge plasma effect on conical shock wave: M = 2.5 flow. AIAA J., 41: 465-469. doi: 10.2514/2.1968
    [83]
    Reedy T M, Kale N V, Dutton C, Elliott G S. 2013. Experimental characterization of a pulsed plasma jet. AIAA J., 51: 2027-2031. doi: 10.2514/1.J052022
    [84]
    Riherd M, Roy S. 2013. Damping Tollmien–Schlichting waves in a boundary layer using plasma actuators. J. Phys. D. :Appl. Phys., 46: 5203.
    [85]
    Roth J R, Sherman D M, Wilkinson S P. 2000. Electrohydrodynamic flow control with a glow-discharge surface plasma. AIAA J, 38: 1166-1172. doi: 10.2514/2.1110
    [86]
    Roth J R, Sherman D M. 1998. Boundary layer flow control with a one atmosphere uniform glow discharge surface plasma// NASA Langley Technical Report Server, 1998-0328
    [87]
    Roth J R. 1995. Investigation of a uniform glow discharge. Plasma in Atmospheric Air, ADA296928.
    [88]
    Saddoughi S, Bennett G, Boespflug M. 2014. Experimental investigation of tip clearance flow in a transonic compressor with and without plasma actuators. J. Turbomach., 137: 041008.
    [89]
    Schuele C Y, Corke T C, Matlist. 2013. Control of stationary cross-flow modes in a Mach 3.5 boundary layer using patterned passive and active roughness. J. Fluid Mech., 718: 5-38. doi: 10.1017/jfm.2012.579
    [90]
    Shang J S. 2002. Plasma injection for hypersonic blunt-body drag reduction. AIAA J., 40: 1178-1186. doi: 10.2514/2.1769
    [91]
    Shin Y J, Kim H J, Kim K H. 2021. Development of one-dimensional analytical model for a spark jet actuator. AIAA J., 59: 1055-1074. doi: 10.2514/1.J059619
    [92]
    Shneider M N, Macheret S O, Zaidi S H, Girgis I G, Miles R B. 2008. Virtual shapes in supersonic flow control with energy addition. J. Propul. Power, 24: 900-915. doi: 10.2514/1.34136
    [93]
    Sidorenko A, Budovsky A D, Pushkarev A V. 2008. Flight testing of DBD plasma separation control system// 46th AIAA Aerospace Sciences Meeting and Exhibit, 2008-373
    [94]
    Soloviev V, Krivtsov V. 2015. Analytical and numerical estimation of the body force and heat sources generated by the surface dielectric barrier discharge powered by alternating voltage// 6th European Conf. for Aeronautics and Space Science, EUCA-SS2015.
    [95]
    Starikovskii A Y, Nikipelov A, Nudnova M, Roupassov D. 2009. SDBD plasma actuator with nanosecond pulse-periodic discharge. Plasma Sources Sci. T., 18: 034015. doi: 10.1088/0963-0252/18/3/034015
    [96]
    Su Z, Li J. 2018. UAV flight test of plasma slats and ailerons with microsecond dielectric barrier discharge. Chin. Phys., 27: 105205. doi: 10.1088/1674-1056/27/10/105205
    [97]
    Sun Q, Cheng B Q, Li Y H, Kong W S, Zhu Y F, Jin D. 2013. Computation and experimental analysis of Mach 2 air flow over a blunt body with plasma aerodynamic actuation. Sci. China Technol. Sc., 56: 795-802. doi: 10.1007/s11431-013-5177-6
    [98]
    Tang M X, Wu Y, Guo S G, Liang H, Luo Y H. 2020a. Compression ramp shock wave/boundary layer interaction control with high-frequency streamwise pulsed spark discharge array. Phys. Fluids, 32: 121704. doi: 10.1063/5.0031839
    [99]
    Tang M X, Wu Y, Guo S G, Sun Z Z, Luo Z B. 2020b. Effect of the streamwise pulsed arc discharge array on shock wave/boundary layer interaction control. Phys. Fluids, 32: 076104. doi: 10.1063/5.0011040
    [100]
    Thomas F O, Corke T C, Duong A, Midya S, Yates K. 2019. Turbulent drag reduction using pulsed-DC plasma actuation. J. Phys. D. Appl. Phys., 52: 434001. doi: 10.1088/1361-6463/ab3388
    [101]
    Ullmer D, Peschke P, Terzis A. 2015. Impact of ns-DBD plasma actuation on the boundary layer transition using convective heat transfer measurements. J. Phys. D, 48: 365203. doi: 10.1088/0022-3727/48/36/365203
    [102]
    Unfer T, Boeuf P. 2009. Modelling of a nanosecond surface discharge actuator. J. Phys. D. Appl. Phys., 42: 194017. doi: 10.1088/0022-3727/42/19/194017
    [103]
    Unfer T, Boeuf P. 2010. Modeling and comparison of sinusoidal and nanosecond pulsed surface dielectric barrier discharges for flow control. Plasma Phys. Control. Fusion, 52: 124019. doi: 10.1088/0741-3335/52/12/124019
    [104]
    Vo H D. 2010. Rotating stall suppression in axial compressors with casing plasma actuation. J. Propul. Power, 26: 808-818. doi: 10.2514/1.36910
    [105]
    Wang L, Xia Z X, Luo Z B. 2014. Three-electrode plasma synthetic jet actuator for high-speed flow control. AIAA J., 52: 879-882. doi: 10.2514/1.J052686
    [106]
    Webb N, Clifford C, Samimy M. 2013. Control of oblique shock wave/boundary layer interactions using plasma actuators. Exp. Fluids, 54: 1545. doi: 10.1007/s00348-013-1545-z
    [107]
    Wei B, Wu Y, Liang H. 2020. Flow control on a high-lift wing with microsecond pulsed surface dielectric barrier discharge actuator. Aerosp. Sci. Technol. , 96: 105584
    [108]
    White A R, Subramaniam V V. 2001. Shock propagation through a low-pressure glow discharge in argon. J. Thermophys. Heat Transfer, 15: 491-496. doi: 10.2514/2.6638
    [109]
    Wu Y, Li Y H, Jia M, Song H M, Guo Z G, Zhu X M, Pu Y K. 2008. Influence of operating pressure on surface dielectric barrier discharge plasma aerodynamic actuation characteristics. Appl. Phys. Lett., 93: 031503. doi: 10.1063/1.2964193
    [110]
    Wu Y, Li Y H, Liang H. 2014. Nanosecond pulsed discharge plasma actuation: characteristics and flow control performance// 45th AIAA Plasma Dynamics and Lasers Conference, 2014-2118
    [111]
    Wu Y, Zhao X H, Li Y H. 2012. Corner separation control in a highly loaded compressor cascade using plasma aerodynamic actuation. R. ASME., GT2012-69196
    [112]
    Yadala S, Hehner M T, Serpieri J, et al. 2018. Experimental control of swept-wing transition through base-flow modification by plasma actuators. J. Fluid. Mech., 844: 268-279.
    [113]
    Yang G, Yao Y, Gan, T, Lu L. 2016. Large-eddy simulation of shock-induced flow separation control using Spark Jet concept// 54th AIAA Aerospace Sciences Meeting, 2016-0045
    [114]
    Zhang H D, Wu Y, Li Y H. 2019a. Control of compressor tip leakage flow using plasma actuation. Aerosp. Sci. Technol., 86: 244-255.
    [115]
    Zhang H D, Wu Y, Li Y H. 2019b. Mechanism of compressor airfoil boundary layer flow control using nanosecond plasma actuation. Int. J. Heat Fluid Flow, 80: 108502. doi: 10.1016/j.ijheatfluidflow.2019.108502
    [116]
    Zhang H D, Wu Y, Yu X, Li Y H, Liu B. 2019c. Experimental investigation on the plasma flow control of axial compressor rotating stall// ASME Turbo Expo: Turbomachinery Technical Conference and Exposition, GT2019-90609
    [117]
    Zhang H D, Yu X J, Liu B J, Wu Y, Li Y H. 2017a. Control of corner separation with plasma actuation in a high-speed compressor cascade. Appl. Sci., 7: 465. doi: 10.3390/app7050465
    [118]
    Zhang Y, Li C, Lee C. 2020. Influence of glow discharge on evolution of disturbance in a hypersonic boundary layer: The effect of second mode. Phys. Fluids, 32: 071702. doi: 10.1063/5.0011299
    [119]
    Zhang Z B, Wu Y, Jia M, Song H M. 2017b. The multichannel discharge plasma synthetic jet actuator. Sensor Actuat. A-Phys., 253: 112-117. doi: 10.1016/j.sna.2016.11.011
    [120]
    Zhang Z, Wu Y, Jia M, Zong H, Cui W, Liang H, Li Y. 2015. Influence of the discharge location on the performance of a three-electrode plasma synthetic jet actuator. Sens. Actuators A:Phys., 235: 71-79. doi: 10.1016/j.sna.2015.09.019
    [121]
    Zhao G, Li Y, Liang H. 2015. Control of vortex on a non-slender delta wing by a nanosecond pulse surface dielectric barrier discharge. Exp. Fluids, 56: 1864. doi: 10.1007/s00348-014-1864-8
    [122]
    Zhao X H, Li Y H, Wu Y. 2012a. Investigation of end-wall flow behavior with plasma flow control on a highly loaded compressor cascade. J. Therm. Sci., 21: 295-301. doi: 10.1007/s11630-012-0547-0
    [123]
    Zhao X H, Li Y H, Wu Y. 2012b. Numerical investigation of flow separation control on a highly loaded compressor cascade by plasma aerodynamic actuation. Chin. J. Aeronaut., 25: 349-360. doi: 10.1016/S1000-9361(11)60396-8
    [124]
    Zhao X H, Wu Y, Li Y H. 2012c. Topological analysis of plasma flow control on corner separation in a highly loaded compressor cascade. Acta Mech. Sin., 28: 1277-1286. doi: 10.1007/s10409-012-0152-1
    [125]
    Zhao Z, Cui Y D. 2018. On the boundary flow using pulsed nanosecond DBD plasma actuators. Mod. Phys. Lett. B, 32: 1840035.
    [126]
    Zhou Y, Xia Z, Luo Z, Wang L. 2017. Effect of three-electrode plasma synthetic jet actuator on shock wave control. Science China Technological Sciences, 60: 146-152. doi: 10.1007/s11431-016-0248-4
    [127]
    Zhu Y, Wu Y. 2020. The secondary ionization wave and characteristic map of surface discharge plasma in a wide time scale. New. J. Phys., 22: 103060. doi: 10.1088/1367-2630/abc2e7
    [128]
    Zhu Y, Shcherbanev S, Baron B, Starikovskaia S. 2017. Nanosecond surface dielectric barrier discharge in atmospheric pressure air: I. measurements and 2D modeling of morphology, propagation and hydrodynamic perturbations. Plasma Sources Sci. Technol., 26: 125004. doi: 10.1088/1361-6595/aa9304
    [129]
    Zhu Y, Wu Y, Cui W, et al. 2013. Modelling of plasma aerodynamic actuation driven by nanosecond SDBD discharge. J. Phys. D. Appl. Phys., 46: 355205. doi: 10.1088/0022-3727/46/35/355205
    [130]
    Zong H H, Wu Y, Jia M, Song H M, Liang H, Li Y H, Zhang Z B. 2015a. Influence of geometrical parameters on performance of plasma synthetic jet actuator. J. Phys. D:Appl. Phys., 49: 0255041.
    [131]
    Zong H H, Wu Y, Li Y H, Song H M, Zhang Z B, Jia M. 2015b. Analytic model and frequency characteristics of plasma synthetic jet actuator. Phys. Fluids, 27: 027105. doi: 10.1063/1.4908071
    [132]
    Zong H, Kotsonis M. 2016. Characterisation of plasma synthetic jet actuators in quiescent flow. J. Phys. D:Appl. Phys., 49: 335202. doi: 10.1088/0022-3727/49/33/335202
    [133]
    Zong H, Kotsonis M. 2017a. Effect of slotted exit orifice on performance of plasma synthetic jet actuator. Exp. Fluids, 58: 17. doi: 10.1007/s00348-016-2299-1
    [134]
    Zong H, Kotsonis M. 2017b. Interaction between plasma synthetic jet and subsonic turbulent boundary layer. Phys. Fluids, 29: 045104. doi: 10.1063/1.4979527
    [135]
    Zong H, Kotsonis M. 2018. Formation, evolution and scaling of plasma synthetic jets. J. Fluid Mech., 837: 147-181. doi: 10.1017/jfm.2017.855
    [136]
    Zong H, van Pelt, Kotsonis. T. 2018. Airfoil Flow Separation control with plasma synthetic jets at moderate Reynolds number. Exp. Fluids, 59: 169. doi: 10.1007/s00348-018-2624-y
    [137]
    Zong H, Kotsonis M. 2019. Effect of velocity ratio on the interaction between plasma synthetic jets and turbulent cross-flow. J. Fluid Mech., 865: 928-962. doi: 10.1017/jfm.2019.93
    [138]
    Zong H, Kotsonis M. 2020. Three-dimensional vortical structures generated by plasma synthetic jets in crossflow. Phys. Fluids, 32: 061701. doi: 10.1063/5.0009530
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