进气道等离子体/磁流体流动控制研究进展
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摘要
为实现高速飞行器的宽速域飞行,如何保证进气道在非设计状态下的性能至关重要。相比于传统被动控制方式,等离子体/磁流体流动控制技术作为新概念主动流动控制技术,由于其具有结构简单,快速响应,并可根据实际飞行条件进行反馈控制等优势,在国内外上得到了广泛关注。本文介绍了等离子体/磁流体在高超/超声速进气道的主要应用方式与等离子体/磁流体建模方法。当进气道处于超临界状态时,等离子体/磁流体流动控制主要通过热阻塞效应产生虚拟型面,从而将激波系推回至唇口,该技术有望在需要短时间流动控制的高马赫数导弹上走向工程应用;由于等离子体/磁流体激励器与壁面平齐安装,对于高超声速飞行条件,相比于粗糙元其对热防护的要求较低,并且通过超声速风洞实验初步证明了通过高频激励对边界层施加扰动的可行性,需要从稳定性理论的角度对其物理机制进行研究。在后续发展中需要进一步创新等离子体产生技术及激励方式,发展等离子体与流的全耦合计算模型等离子体与流的全耦合计算模型与高效算法,为指导工程应用提供依据.
In order to realize wide-speed-range flight of high-speed vehicle, it is of great importance to maintain the performance of inlet at off-design. Compared with traditional passive control methods, plasma and magnetohydrodynaimic(MHD) flow control are novel active flow control methods, and they have attracted extensive attention worldwide,as a result of some advantages, such as simple structure, fast response and feedback control based on actual flight condition, etc. In this paper, the main applications of plasma and MHD in hyper/supersonic inlet and dynamics models are introduced. When the inlets are in supercritical state, the shockwaves can be push back to cowl as a result of the virtual surface produced by plasma and MHD, which is based on the effect of thermal chocking. This technology is expected to applied on the hypersonic missile if only short-time flow control is required. The plasma and MHD actuators can be mounted flush on the wall, so that its requirement for thermal protection is less than that of roughness at hypersonic flight condition. The applications of high-frequency plasma and MHD actuation to produce disturbances in boundary layer have been validated through supersonic wind tunnel experiment, and the physical mechanism can be interpreted from the point of stability theory. The innovative developments of plasma source technology and the way of actuation, as well as coupled model of plasma and fluid dynamics and efficient algorithms are required in future, which can provide guidance for engineering application.
In order to realize wide-speed-range flight of high-speed vehicle, it is of great importance to maintain the performance of inlet at off-design. Compared with traditional passive control methods, plasma and magnetohydrodynaimic(MHD) flow control are novel active flow control methods, and they have attracted extensive attention worldwide,as a result of some advantages, such as simple structure, fast response and feedback control based on actual flight condition, etc. In this paper, the main applications of plasma and MHD in hyper/supersonic inlet and dynamics models are introduced. When the inlets are in supercritical state, the shockwaves can be push back to cowl as a result of the virtual surface produced by plasma and MHD, which is based on the effect of thermal chocking. This technology is expected to applied on the hypersonic missile if only short-time flow control is required. The plasma and MHD actuators can be mounted flush on the wall, so that its requirement for thermal protection is less than that of roughness at hypersonic flight condition. The applications of high-frequency plasma and MHD actuation to produce disturbances in boundary layer have been validated through supersonic wind tunnel experiment, and the physical mechanism can be interpreted from the point of stability theory. The innovative developments of plasma source technology and the way of actuation, as well as coupled model of plasma and fluid dynamics and efficient algorithms are required in future, which can provide guidance for engineering application.
引文
1 Vanwie DM,Nedungadi A.Plasma aerodynamic flow control for hypersonic inlets.AIAA Paper 2004-4129,2004
2李益文,张百灵,李应红等.磁流体动力学在航空工程中的应用与展望.力学进展,2017,47:201713(Li Yiwen,Zhang Bailing,Li Yinghong,et,al.Review on the application and prospect of magnetohydrodynamic in aeronautical engineering.Advances in Mechanics,2017,47:201713(in Chinese))
3吴其芬,李桦.磁流体力学.长沙:国防科技大学出版社,2007(Wu Qifen,Li Hua.Magneto-Fluid Mechanics.Changsha:National University of Defense Technology Press,2007(in Chinese))
4郭永怀.现代空气动力学的问题.科学通报,1957,2(10):289-295
5 Bobashev SV,D’yakonova EA,Erofeev AB,et al.Influence of MHD interaction on shock wave structure in supersonic diffuser//2nd Workshop on Magneto-Plasma-Aerodynamics in Aerospace Applications,Moscow,2000
6 Bobashev SV,Erofeev AB,Lapushkina TA,et al.Strong action of magnetic and electric fields on inlet shock configuration in diffuser.AIAA Paper 2001-2878,2001
7 Bobashev SV,Erofeev AV,Lapushkina TA,et al.Experiments on MHD control of attached shocks in diffuser.AIAA Paper 2003-0169,2003
8 Macheret SO,Shneider MN,Miles RB.External supersonic flow and scramjet inlet control by MHD with electron beam ionization.AIAA Paper 2001-0492,2001
9 Shneider MN,Macheret SO,Miles RB.Comparative analysis of MHD and plasma methods of scramjet inlet control.AIAA Paper2003-170,2003
10李益文,樊昊,张百灵等.超声速非平衡电离磁流体流动控制试验与数值模拟,航空学报,2017,38(3):146-155(Li Yiwen,Fan Hao,Zhang Bailing,et al.Test and numerical simulation on magnetohydrodynamic flow control with nonequilibrium ionization.Acta Aeronautica ET Astronautica Sinica,2017,38(3):146-155(in Chinese))
11 Leonov SB,Bityurin V,Yarantsev D.The effect of plasma induced separation.AIAA Paper 2003-3853,2003
12 Leonov SB,Yarantsev DA.Near-surface electrical discharge in supersonic airflow:properties and flow control.Journal of Propulsion and Power,2008,24(6):1168-1181
13 Leonov SB,Firsov AA,Yarantsev DA,et al.Flow control in model supersonic inlet by electrical discharge.AIAA Paper 2009-7367,2009
14 Leonov SB,Firsov AA,Yarantsev DA,et al.Plasma effect on shocks configuration in compression ramp.AIAA Paper 2011-2362,2011
15 Falempin F,Firsov AA,Yarantsev DA,et al.Plasma control of shock wave configuration in off-design mode of M=2 inlet.Exp Fluids,2015,56(3):1-10
16 Miles RB,Macheret SO,Shneider MN,et al.Plasma-enhanced hypersonic performance enabled by MHD power extraction.AIAAPaper,2005-561,2005
17 Zaidi SH,Smith T,Macheret S,et al.Snowplow surface discharge in magnetic field for high speed boundary layer control.AIAA Paper2006-1006,2006
18 Kalra CS,Zaidi SH,Miles RB,et al.Shockwave-turbulent boundary layer interaction control using magnetically driven surface discharges.Exp Fluids,2011,50(3):547-559
19 Kalra CS,Zaidi SH,Miles RB.Velocity measurements in synthetic jet using magnetically driven surface discharges.AIAA Paper 2010-831,2010
20 Macheret SO.Physics of magnetically accelerated nonequilibrium surface discharges in high-speed flow.AIAA Paper 2006-1005,2006
21 Bisek NJ,Rizzetta DP,Poggie J.Plasma control of a turbulent shock boundary-layer interaction.AIAA Journal,2013,51(8):1789-1804
22苏纬仪,陈立红,张新宇.MHD控制超声速边界层的理论研究和数值分析.力学学报,2010,42(4):782-788(Su Weiyi,Chen Lihong,Zhang Xinyu.Theoretical and applied mechanics,physics and numerical simulations of MHD accelerated supersonic boundary layer.Chinese Journal of Theoretical and Applied Mechanics,2010,42(4):782-788(in Chinese))
23刘成,叶正寅,叶坤.转捩位置对全动舵面热气动弹性的影响.力学学报,2017,49(4):802-810(Liu Cheng,Ye Zhengyin,Ye Kun.The effect of transition location on aerothermoelasticity of a hypersonic all-movable centrol surface.Chinese Journal of Theoretical and Applied Mechanics,2017,49(4):802-810(in Chinese))
24叶友达,张涵信,蒋勤学等.近空间高超声速飞行器气动特性研究的若干关键问题.力学学报,2018,50(6):1292-1310(Ye Youda,Zhang Hanxin,Jiang Qinxue,et al.Some key problems in the study of aerodynamic characteristics of near-space hypersonic vehicles.Chinese Journal of Theoretical and Applied Mechanics,2018,50(6):1292-1310(in Chinese))
25童福林,李欣,于长平等.高超声速激波湍流边界层干扰直接数值模拟研究.力学学报,2018,50(2):197-208(Tong Fulin,Li Xin,Yu Changping,et al.Direct numerical simulation of hypersonic shock wave and turbulent boundary layer interactions.Chinese Journal of Theoretical and Applied Mechanics,2018,50(2):197-208(in Chinese))
26 Wang YT,Li YW,Xiao LH,et al.Similarity-solution-based improvement ofγ-Reθt model for hypersonic transition prediction.International Journal of Heat and Mass Transfer,2018,124(9):491-503
27 Berry SA,Nowak RJ,Horvath TJ.Boundary layer control for hypersonic air breathing vehicles,AIAA Paper 2004-2246,2004
28赵慧勇,周瑜,倪鸿礼等.高超声速进气道边界层强制转捩试验.实验流体力学,2012,26(1):1-6(Zhao Huiyong,Zhou Yu,Ni Hongli,et al.Test of Forced boundary-layer transition on hypersonic inlet.Journal of Experiments in Fluid Mechanics,2012,26(1):1-6(in Chinese))
29赵俊波,沈清,张红军等.基于T-S波谐频共振的超燃进气道边界层转捩.航空动力学报,2010,25(11):2420-2424(Zhao Junbo,Shen Qing,Zhang Hongjun,et al.Boundary layer reaserch of scramjet inlet based on T-S wave syntony.Jounral of Aerospace Power,2010,25(11):2420-2424(in Chinese))
30张红军,沈清.新型高超声速进气道边界层人工转捩方法研究.实验流体力学,2016,30(2):75-78(A new method of artificial boundary layer transition for hypersonic inlet.Experiments in Fluid Mechanics,2016,30(2):75-78(in Chinese))
31 Rossow VJ.On flow of electrically conducting fluids over a flat plate in the presence of a transverse magnetic field.NACA TN 3971,May1957
32 Rossow VJ.Boundary-layer stability diagrams for electrically conducting fluids in the presence of a magnetic field.NACA TN 4282,August,1958
33 Kimmel RL.Aspects of hypersonic boundary-layer transition control.AIAA Paper 2003-772,2003
34 Cheng F,Zhong X,Gogineni S,et al.Effect of appl ied magnetic field on the instability of Mach 4.5 boundary-layer over a flat plate.AIAA Paper 2002-0351,2002
35 Palm P,Meyer R,Pl¨onjes E,et al.MHD effect on a supersonic weakly ionized flow.AIAA Paper 2002-2246,2002
36 Yan H,Gaitonde D.Effect of thermally induced perturbation in supersonic boundary layers.Physics of Fluids,2010,22:064101
37 Yan H,Gaitonde D.Parametric study of pulsed thermal bumps in supersonic boundary layer.Shock Waves,2011,21:411-423
38 Polivanov PA,Sidorenko AA,Maslov AA.Artificial turbulization of the supersonic boundary layer by dielectric barrier discharge//29th Congress of International Council of the Aeronautical Science,Petersburg Russia,2014
39 Keller MA,Kloker MJ,Kirilovskiy SV,et al.Study of flow control by localized volume heating in hypersonic boundary layers.CEASSpace Journal,2014,6:119-132
40 Ladoon DW,Schneider SP.Measurements of controlled wave packets at Mach 4 on a cone at angle of attack.AIAA Paper,1997
41 Borg MP.Laminar instability and transition on the X-51A.[PhDThesis].Purdue University,2009
42 Houpt A,Leonov SB,Falempin F.Control of Hypersonic BL Transition by electrical discharge(feasibility study).AIAA Paper 2015-3602,2015
43 Houpt A,Gordeyev S,Juliano T,et al.Optical measurement of transient plasma impact on corner separation in M=4.5 airflow.AIAAPaper 2016-2160,2016
44 Houpt A,Hedlund BE,Gordeyev SV,et al.Transient plasma impact on spectra of flow disturbances in a corner separation zone at Mach4.5.AIAA Paper 2016-4304,2016
45 Soloviev VR,Krivtsov VM.Surface barrier discharge modelling for aerodynamic applications.Journal of Physics D:Applied Physics,2009,42(12):125208-1-13
46 Soloviev VR,Konchakov AM,Krivtsov VM,et al.Numerical simulation of a surface barrier discharge in air.Plasma Physics Reports,2008,43(7):594-608
47 Soloviev VR,Krivtsov VM,Shcherbanev SA,et al.Evolution of nanosecond surface dielectric barrier discharge for negative polarity of a voltage pulse.Plasma Sources Science Technology,2017,26(1):014001-1-12
48 Shang JS,Surzhikov ST,Kimmel R,et al.Mechanisms of plasma actuators for hypersonic flow control.Progress in Aerospace Sciences,2005,41(8):642-668
49 Shang JS,Kimmel R,Menart J,et al.Hypersonic flow control using surface plasma actuator.Journal of Propulsion and Power,2008,24(5):923-934
50 Abdollahzadeh M,Pascoa JC,Oliveira PJ.Implementation of the classical plasma-fluid model for simulation of dielectric barrier discharge(DBD)actuators in OpenFOAM.Computer&Fluids,2016,128(10):77-90
51 Xu SY,Cai JS,Zhang ZK,et al.Investigation of the electrode surface geometry effects driven by nanosecond-pulsed surface dielectric barrier discharge.Journal of Physics D:Applied Physics,2017,50(18):185201-1-12
52 Xu SY,Cai JS,Li J.Modeling and simulation of plasma gas flow driven by a single nanosecond-pulsed dielectric barrier discharge.Physics of Plasmas,2016,23(10):103510-1-10
53 Popov NA.Fast gas heating in a nitrogen-oxygen discharge plasma:I.Kinetic mechanism.Journal of Physics D:Applied Physics,2011,44(28):285201-1-16
54 Takashima K,Yin Z,Adamovich IV.Measurements and kinetic modeling of energy coupling in volume and surface nanosecond pulse discharges.Plasma Sources Science Technology,2013,22(1):015013-1-16
55 Gaitonde DV,Poggie J.Elements of a numerical procedure for 3-DMGD flow control analysis.AIAA Paper 2002-0198,2002
56 Bisek NJ,Rizzetta DP,Poggie J.Plasma control of a turbulent shock boundary-layer interaction.AIAA Journal,2013,51(8):1789-1804
57 Ishikawa M,Itoh K.Three dimensional constricted electric current near anode and cathode of faraday MHD generator.Energy Conversion and Management,2003,44(13):2111-2124
58 Itoh K,Ishikawa M.Three-dimensional analyses of phenomena near anode of MHD generator with high temperature,high velocity,and strong MHD interaction.AIAA Paper 2001-2810,2001
59 Lu HY,Lee CH,Dong HT,et al.Numerical analysis and optimization of three-dimensional MHD controlled inlets.AIAA Paper2008-1390,2008
60 Lu HY,Lee CH.Simulation of three-dimensional nonideal MHDflow at high magnetic Reynolds number.Science in China Series E:Technological Sciences,2010,40(5):206-212
61田正雨,张康平,丁国昊等.MHD数值模拟中清除伪磁场散度方法.计算物理,2009,26(1):78-86(Tian Zhengyu,Zhang Kangping,Ding Guohao,et al.Spurious magnetic field divergence cleaning in magnetohydrodynamic simulation.Chinese Journal of Computational Physics,2009,26(1):78-86(in Chinese))
2李益文,张百灵,李应红等.磁流体动力学在航空工程中的应用与展望.力学进展,2017,47:201713(Li Yiwen,Zhang Bailing,Li Yinghong,et,al.Review on the application and prospect of magnetohydrodynamic in aeronautical engineering.Advances in Mechanics,2017,47:201713(in Chinese))
3吴其芬,李桦.磁流体力学.长沙:国防科技大学出版社,2007(Wu Qifen,Li Hua.Magneto-Fluid Mechanics.Changsha:National University of Defense Technology Press,2007(in Chinese))
4郭永怀.现代空气动力学的问题.科学通报,1957,2(10):289-295
5 Bobashev SV,D’yakonova EA,Erofeev AB,et al.Influence of MHD interaction on shock wave structure in supersonic diffuser//2nd Workshop on Magneto-Plasma-Aerodynamics in Aerospace Applications,Moscow,2000
6 Bobashev SV,Erofeev AB,Lapushkina TA,et al.Strong action of magnetic and electric fields on inlet shock configuration in diffuser.AIAA Paper 2001-2878,2001
7 Bobashev SV,Erofeev AV,Lapushkina TA,et al.Experiments on MHD control of attached shocks in diffuser.AIAA Paper 2003-0169,2003
8 Macheret SO,Shneider MN,Miles RB.External supersonic flow and scramjet inlet control by MHD with electron beam ionization.AIAA Paper 2001-0492,2001
9 Shneider MN,Macheret SO,Miles RB.Comparative analysis of MHD and plasma methods of scramjet inlet control.AIAA Paper2003-170,2003
10李益文,樊昊,张百灵等.超声速非平衡电离磁流体流动控制试验与数值模拟,航空学报,2017,38(3):146-155(Li Yiwen,Fan Hao,Zhang Bailing,et al.Test and numerical simulation on magnetohydrodynamic flow control with nonequilibrium ionization.Acta Aeronautica ET Astronautica Sinica,2017,38(3):146-155(in Chinese))
11 Leonov SB,Bityurin V,Yarantsev D.The effect of plasma induced separation.AIAA Paper 2003-3853,2003
12 Leonov SB,Yarantsev DA.Near-surface electrical discharge in supersonic airflow:properties and flow control.Journal of Propulsion and Power,2008,24(6):1168-1181
13 Leonov SB,Firsov AA,Yarantsev DA,et al.Flow control in model supersonic inlet by electrical discharge.AIAA Paper 2009-7367,2009
14 Leonov SB,Firsov AA,Yarantsev DA,et al.Plasma effect on shocks configuration in compression ramp.AIAA Paper 2011-2362,2011
15 Falempin F,Firsov AA,Yarantsev DA,et al.Plasma control of shock wave configuration in off-design mode of M=2 inlet.Exp Fluids,2015,56(3):1-10
16 Miles RB,Macheret SO,Shneider MN,et al.Plasma-enhanced hypersonic performance enabled by MHD power extraction.AIAAPaper,2005-561,2005
17 Zaidi SH,Smith T,Macheret S,et al.Snowplow surface discharge in magnetic field for high speed boundary layer control.AIAA Paper2006-1006,2006
18 Kalra CS,Zaidi SH,Miles RB,et al.Shockwave-turbulent boundary layer interaction control using magnetically driven surface discharges.Exp Fluids,2011,50(3):547-559
19 Kalra CS,Zaidi SH,Miles RB.Velocity measurements in synthetic jet using magnetically driven surface discharges.AIAA Paper 2010-831,2010
20 Macheret SO.Physics of magnetically accelerated nonequilibrium surface discharges in high-speed flow.AIAA Paper 2006-1005,2006
21 Bisek NJ,Rizzetta DP,Poggie J.Plasma control of a turbulent shock boundary-layer interaction.AIAA Journal,2013,51(8):1789-1804
22苏纬仪,陈立红,张新宇.MHD控制超声速边界层的理论研究和数值分析.力学学报,2010,42(4):782-788(Su Weiyi,Chen Lihong,Zhang Xinyu.Theoretical and applied mechanics,physics and numerical simulations of MHD accelerated supersonic boundary layer.Chinese Journal of Theoretical and Applied Mechanics,2010,42(4):782-788(in Chinese))
23刘成,叶正寅,叶坤.转捩位置对全动舵面热气动弹性的影响.力学学报,2017,49(4):802-810(Liu Cheng,Ye Zhengyin,Ye Kun.The effect of transition location on aerothermoelasticity of a hypersonic all-movable centrol surface.Chinese Journal of Theoretical and Applied Mechanics,2017,49(4):802-810(in Chinese))
24叶友达,张涵信,蒋勤学等.近空间高超声速飞行器气动特性研究的若干关键问题.力学学报,2018,50(6):1292-1310(Ye Youda,Zhang Hanxin,Jiang Qinxue,et al.Some key problems in the study of aerodynamic characteristics of near-space hypersonic vehicles.Chinese Journal of Theoretical and Applied Mechanics,2018,50(6):1292-1310(in Chinese))
25童福林,李欣,于长平等.高超声速激波湍流边界层干扰直接数值模拟研究.力学学报,2018,50(2):197-208(Tong Fulin,Li Xin,Yu Changping,et al.Direct numerical simulation of hypersonic shock wave and turbulent boundary layer interactions.Chinese Journal of Theoretical and Applied Mechanics,2018,50(2):197-208(in Chinese))
26 Wang YT,Li YW,Xiao LH,et al.Similarity-solution-based improvement ofγ-Reθt model for hypersonic transition prediction.International Journal of Heat and Mass Transfer,2018,124(9):491-503
27 Berry SA,Nowak RJ,Horvath TJ.Boundary layer control for hypersonic air breathing vehicles,AIAA Paper 2004-2246,2004
28赵慧勇,周瑜,倪鸿礼等.高超声速进气道边界层强制转捩试验.实验流体力学,2012,26(1):1-6(Zhao Huiyong,Zhou Yu,Ni Hongli,et al.Test of Forced boundary-layer transition on hypersonic inlet.Journal of Experiments in Fluid Mechanics,2012,26(1):1-6(in Chinese))
29赵俊波,沈清,张红军等.基于T-S波谐频共振的超燃进气道边界层转捩.航空动力学报,2010,25(11):2420-2424(Zhao Junbo,Shen Qing,Zhang Hongjun,et al.Boundary layer reaserch of scramjet inlet based on T-S wave syntony.Jounral of Aerospace Power,2010,25(11):2420-2424(in Chinese))
30张红军,沈清.新型高超声速进气道边界层人工转捩方法研究.实验流体力学,2016,30(2):75-78(A new method of artificial boundary layer transition for hypersonic inlet.Experiments in Fluid Mechanics,2016,30(2):75-78(in Chinese))
31 Rossow VJ.On flow of electrically conducting fluids over a flat plate in the presence of a transverse magnetic field.NACA TN 3971,May1957
32 Rossow VJ.Boundary-layer stability diagrams for electrically conducting fluids in the presence of a magnetic field.NACA TN 4282,August,1958
33 Kimmel RL.Aspects of hypersonic boundary-layer transition control.AIAA Paper 2003-772,2003
34 Cheng F,Zhong X,Gogineni S,et al.Effect of appl ied magnetic field on the instability of Mach 4.5 boundary-layer over a flat plate.AIAA Paper 2002-0351,2002
35 Palm P,Meyer R,Pl¨onjes E,et al.MHD effect on a supersonic weakly ionized flow.AIAA Paper 2002-2246,2002
36 Yan H,Gaitonde D.Effect of thermally induced perturbation in supersonic boundary layers.Physics of Fluids,2010,22:064101
37 Yan H,Gaitonde D.Parametric study of pulsed thermal bumps in supersonic boundary layer.Shock Waves,2011,21:411-423
38 Polivanov PA,Sidorenko AA,Maslov AA.Artificial turbulization of the supersonic boundary layer by dielectric barrier discharge//29th Congress of International Council of the Aeronautical Science,Petersburg Russia,2014
39 Keller MA,Kloker MJ,Kirilovskiy SV,et al.Study of flow control by localized volume heating in hypersonic boundary layers.CEASSpace Journal,2014,6:119-132
40 Ladoon DW,Schneider SP.Measurements of controlled wave packets at Mach 4 on a cone at angle of attack.AIAA Paper,1997
41 Borg MP.Laminar instability and transition on the X-51A.[PhDThesis].Purdue University,2009
42 Houpt A,Leonov SB,Falempin F.Control of Hypersonic BL Transition by electrical discharge(feasibility study).AIAA Paper 2015-3602,2015
43 Houpt A,Gordeyev S,Juliano T,et al.Optical measurement of transient plasma impact on corner separation in M=4.5 airflow.AIAAPaper 2016-2160,2016
44 Houpt A,Hedlund BE,Gordeyev SV,et al.Transient plasma impact on spectra of flow disturbances in a corner separation zone at Mach4.5.AIAA Paper 2016-4304,2016
45 Soloviev VR,Krivtsov VM.Surface barrier discharge modelling for aerodynamic applications.Journal of Physics D:Applied Physics,2009,42(12):125208-1-13
46 Soloviev VR,Konchakov AM,Krivtsov VM,et al.Numerical simulation of a surface barrier discharge in air.Plasma Physics Reports,2008,43(7):594-608
47 Soloviev VR,Krivtsov VM,Shcherbanev SA,et al.Evolution of nanosecond surface dielectric barrier discharge for negative polarity of a voltage pulse.Plasma Sources Science Technology,2017,26(1):014001-1-12
48 Shang JS,Surzhikov ST,Kimmel R,et al.Mechanisms of plasma actuators for hypersonic flow control.Progress in Aerospace Sciences,2005,41(8):642-668
49 Shang JS,Kimmel R,Menart J,et al.Hypersonic flow control using surface plasma actuator.Journal of Propulsion and Power,2008,24(5):923-934
50 Abdollahzadeh M,Pascoa JC,Oliveira PJ.Implementation of the classical plasma-fluid model for simulation of dielectric barrier discharge(DBD)actuators in OpenFOAM.Computer&Fluids,2016,128(10):77-90
51 Xu SY,Cai JS,Zhang ZK,et al.Investigation of the electrode surface geometry effects driven by nanosecond-pulsed surface dielectric barrier discharge.Journal of Physics D:Applied Physics,2017,50(18):185201-1-12
52 Xu SY,Cai JS,Li J.Modeling and simulation of plasma gas flow driven by a single nanosecond-pulsed dielectric barrier discharge.Physics of Plasmas,2016,23(10):103510-1-10
53 Popov NA.Fast gas heating in a nitrogen-oxygen discharge plasma:I.Kinetic mechanism.Journal of Physics D:Applied Physics,2011,44(28):285201-1-16
54 Takashima K,Yin Z,Adamovich IV.Measurements and kinetic modeling of energy coupling in volume and surface nanosecond pulse discharges.Plasma Sources Science Technology,2013,22(1):015013-1-16
55 Gaitonde DV,Poggie J.Elements of a numerical procedure for 3-DMGD flow control analysis.AIAA Paper 2002-0198,2002
56 Bisek NJ,Rizzetta DP,Poggie J.Plasma control of a turbulent shock boundary-layer interaction.AIAA Journal,2013,51(8):1789-1804
57 Ishikawa M,Itoh K.Three dimensional constricted electric current near anode and cathode of faraday MHD generator.Energy Conversion and Management,2003,44(13):2111-2124
58 Itoh K,Ishikawa M.Three-dimensional analyses of phenomena near anode of MHD generator with high temperature,high velocity,and strong MHD interaction.AIAA Paper 2001-2810,2001
59 Lu HY,Lee CH,Dong HT,et al.Numerical analysis and optimization of three-dimensional MHD controlled inlets.AIAA Paper2008-1390,2008
60 Lu HY,Lee CH.Simulation of three-dimensional nonideal MHDflow at high magnetic Reynolds number.Science in China Series E:Technological Sciences,2010,40(5):206-212
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