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Pulsed arc plasma excitation is characterized by strong local heating effect and wide disturbance range, and it has a broad application prospect in supersonic flow control. In this paper, by using electrical parameter measurement system and high speed schlieren technique, we study the electrical and flow field characteristics of pulsed arc plasma excitation under the condition of Ma = 3 incoming flow. The nano-particle planar laser scattering (NPLS) is used to investigate the flow structure of the supersonic flat boundary layer, and the transition characteristics of the boundary layer at different plasma excitation frequencies are studied. The experimental results show that in the flow field with Ma = 3 and the total incoming pressure P0 = 1 atm (1 atm = 1.01 × 105 Pa), the peak voltage of the pulsed arc plasma actuator discharge is 6 kV, the peak current is 70 A, the time scale of the discharge is about 300 ns, the single discharge energy is 70 mJ; the pulsed arc discharge will produce the precursor shock wave with higher velocity and the thermal deposition zone with higher temperature, which will exert continuously disturbance on the boundary layer. The pulsed arc plasma excitation with perturbation can promote the transition of supersonic plate boundary layer. Moreover, the high-frequency impact effect of pulsed discharge can promote the transition to occur ahead of time, and the higher the frequency, the better the effect is. As the excitation frequency increases, the transition position of the boundary layer of the supersonic flat plate moves forward, and the length of the transition area of the boundary layer becomes shorter as the excitation frequency increases. When the excitation frequency is 60 kHz, the length of transition zone is 0 and the thickness of turbulent boundary layer is 25 mm. When a high frequency is applied (f = 40, 60 kHz), the transition path of the boundary layer is that the shock wave generated by the plasma excitation triggers the unstable wave, and the development of unstable waves directly skips the linear growth stage, passes through the bypass and transitions into turbulent flow. The pulsed arc plasma excitation can be used to promote supersonic boundary layer transition.
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Keywords:
- pulsed arc /
- supersonic /
- transition /
- nano-particle planar laser scattering
[1] 陈坚强, 涂国华, 张毅锋, 徐国亮, 袁先旭, 陈诚 2017 空气动力学学报 35 311
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Luo J L, Li C, Xu J 2015 Acta Aeronaut. Astronaut. Sin. 36 39
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[4] 刘向宏, 赖光伟, 吴杰 2018 空气动力学学报 36 196
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[5] 杨武兵, 沈清, 朱德华, 禹旻, 刘智勇 2018 空气动力学学报 36 183
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[6] 付佳, 易仕和, 王小虎, 张庆虎, 何霖 2015 物理学报 64 014704
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Fu J, Yi S H, Wang X H, Zhang Q H, He L 2015 Acta Phys. Sin. 64 014704
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Zhao H Y, Zhou Y, Ni H L, Liu W X 2012 J. Exp. Fluid Mech. 26 1
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Dong H, Liu S C, Geng X, Cheng K M 2018 J. Northwestern Polytech. Univ. 36 137
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[10] 黄勇 2011 实验流体力学 20 59
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Wang J, Li Y H, Chen B Q, Su C B, Song H M, Wu Y 2009 Acta Aeronaut. Astronaut. Sin. 30 1374
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Gan T Ph. D. Dissertation (Xi’an: Air Force Engineering University) (in Chinese)
[20] 唐孟潇 2018 硕士学位论文 (西安: 空军工程大学)
Tang M X 2018 M. S. Thesis (Xian: Air Force Engineering University) (in Chinese)
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图 1 PADPA的工作过程 (a) 施加高电压; (b) 气体击穿; (c) CGB产生
Figure 1. Working process of PADPA: (a) High voltage applied; (b) gas breakdown; (c) CGB generation.
图 2 平板尺寸示意图
Figure 2. Plate size drawing
图 3 PADPA工作示意图
Figure 3. PADPA working diagram
图 4 NPLS系统示意图
Figure 4. NPLS system diagram
图 5 高速纹影系统示意图
Figure 5. Schematic diagram of high-speed schlieren system
图 6 纳秒脉冲电源
Figure 6. Nanosecond pulse power supply
图 7 放电特性 (a) 电压电流波形; (b) 功率波形
Figure 7. Discharge characteristic: (a) Voltage current waveform; (b) power waveform.
图 8 单脉冲电弧放电过程 (a) 电弧形态; (b) 激励区域演化过程
Figure 8. Process of monopulse arc discharge: (a) The shape of arc; (b) the evolution of the excitation area.
图 9 不同激励频率下放电的纹影显示 (a) f = 5 kHz; (b) f = 10 kHz; (c) f = 20 kHz
Figure 9. Schlieren display at different excitation frequencies: (a) f = 5 kHz; (b) f = 10 kHz; (c) f = 20 kHz.
图 10 前驱冲击波速度随时间的变化曲线
Figure 10. Velocity curve of precursor shock wave with time.
图 11 激励器在来流条件下的流场特性演化 (a) f = 10 kHz; (b) f = 20 kHz
Figure 11. Evolution of flow field characteristics of the exciter under incoming flow conditions: (a) f = 10 kHz; (b) f = 20 kHz.
图 12 基准流场图
Figure 12. Basic flow field diagram.
图 13 激励频率为5 kHz时流场图
Figure 13. Flow field diagram when excitation frequency is 5 kHz.
图 14 激励频率为10 kHz时流场图
Figure 14. Flow field diagram when excitation frequency is 10 kHz.
图 15 激励频率为20 kHz时流场图
Figure 15. Flow field diagram when excitation frequency is 20 kHz.
图 16 激励频率为40 kHz时流场图
Figure 16. Flow field diagram when excitation frequency is 40 kHz.
图 17 激励频率为60 kHz时流场图
Figure 17. Flow field diagram when excitation frequency is 60 kHz.
图 18 转捩参数随激励频率的变化 (a) 转捩位置随激励频率的变化; (b) 转捩区长度随激励频率的变化
Figure 18. Transition parameters vary with excitation frequency: (a) Transition position varies with the excitation frequency; (b) length of transition zone varies with the excitation frequency.
图 19 边界层转捩到湍流的5种途径
Figure 19. Five ways for boundary layer transition to turbulence.
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[1] 陈坚强, 涂国华, 张毅锋, 徐国亮, 袁先旭, 陈诚 2017 空气动力学学报 35 311
Google Scholar
Chen J Q, Tu G H, Zhang Y F, Xu GL, Yuan X X, Chen C 2017 Acta Aerodyn. Sin. 35 311
Google Scholar
[2] Tirtey S C, Chazot O, Walpot L 2011 Exp. Fluids 50 407
Google Scholar
[3] 罗金玲, 李超, 徐锦 2015 航空学报 36 39
Google Scholar
Luo J L, Li C, Xu J 2015 Acta Aeronaut. Astronaut. Sin. 36 39
Google Scholar
[4] 刘向宏, 赖光伟, 吴杰 2018 空气动力学学报 36 196
Google Scholar
Liu X H, Lai G W, Wu J 2018 Acta Aerodyn. Sin. 36 196
Google Scholar
[5] 杨武兵, 沈清, 朱德华, 禹旻, 刘智勇 2018 空气动力学学报 36 183
Google Scholar
Yang W B, Shen Q, Zhu D H, Yu W, Liu Z Y 2018 Acta Aerodyn. Sin. 36 183
Google Scholar
[6] 付佳, 易仕和, 王小虎, 张庆虎, 何霖 2015 物理学报 64 014704
Google Scholar
Fu J, Yi S H, Wang X H, Zhang Q H, He L 2015 Acta Phys. Sin. 64 014704
Google Scholar
[7] Li F, Xie S F, Bi Z X 2014 Mod. Def. Technol. 44 705
Google Scholar
[8] 赵慧勇, 周瑜, 倪鸿礼, 刘伟雄 2012 实验流体力学 26 1
Google Scholar
Zhao H Y, Zhou Y, Ni H L, Liu W X 2012 J. Exp. Fluid Mech. 26 1
Google Scholar
[9] 董昊, 刘是成, 耿玺, 程克明 2018 西北工业大学学报 36 137
Google Scholar
Dong H, Liu S C, Geng X, Cheng K M 2018 J. Northwestern Polytech. Univ. 36 137
Google Scholar
[10] 黄勇 2011 实验流体力学 20 59
Google Scholar
Huang Y 2011 J. Exp. Fluid Mech. 20 59
Google Scholar
[11] 王健, 李应红, 程邦勤, 苏长兵, 宋慧敏, 吴云 2009 航空学报 30 1374
Google Scholar
Wang J, Li Y H, Chen B Q, Su C B, Song H M, Wu Y 2009 Acta Aeronaut. Astronaut. Sin. 30 1374
Google Scholar
[12] 宗豪华, 宋慧敏, 梁华, 贾敏, 李应红 2015 推进技术 36 1474
Google Scholar
Zong H H, Song H M, Liang H, Jia M, Li Y H 2015 J. Propuls. Technol. 36 1474
Google Scholar
[13] 张攀峰, 刘爱兵, 王晋军 2011 中国科学:技术科学 32 482
Google Scholar
Zhang D P, Liu A B, Wang J J 2011 Sci. China-Tech. Sci. 32 482
Google Scholar
[14] 陆纪椿, 史志伟, 杜海, 胡亮, 李铮, 宋天威 2016 航空学报 37 1166
Google Scholar
Lu J C, Shi Z W, Du H, Hu L, Li Z, Song T W 2016 Acta Aeronaut. Astronaut. Sin. 37 1166
Google Scholar
[15] Grundmann S, Tropea C 2007 Exp. Fluids 42 653
Google Scholar
[16] Grundmann S, Tropea C 2008 Exp. Fluids 44 795
Google Scholar
[17] [18] Sun Q, Li Y H, Cheng B, Cui W, Liu W D, Xiao Q 2014 Phy. Lett. A 378 2672
Google Scholar
[19] 甘甜 2018 博士学位论文 (西安: 空军工程大学)
Gan T Ph. D. Dissertation (Xi’an: Air Force Engineering University) (in Chinese)
[20] 唐孟潇 2018 硕士学位论文 (西安: 空军工程大学)
Tang M X 2018 M. S. Thesis (Xian: Air Force Engineering University) (in Chinese)
[21] Leonov S, Bityurin V, Savischenko N 2001 39th Aerospace Sciences Meeting and Exhibit Reno, NV, USA, January 8−11, 2001 p21
[22] Gan T, Wu Y, Sun Z Z, Jin D, Song H M, Jia M 2018 Phys. Fluids 30 055107
Google Scholar
[23] Bletzinger P, Ganguly B N, Wie D V 2005 J. Phys. D. Appl. Phys. 38 33
Google Scholar
[24] Webb N, Clifford C, Samimy M 2013 Exp. Fluids 54 1545
Google Scholar
[25] He L 2011 Ph. D. Dissertation (Changsha: National University of Defense Technology) (in Chinese)
[26] 赵云飞, 刘伟, 冈敦殿, 易仕和, 邓小刚 2015 宇航学报 36 739
Google Scholar
Zhao Y F, Liu W, Gang D D, Yi S H, Deng X G 2015 J. Astron. 36 739
Google Scholar
[27] Morkovin M V 1968 Mechanics of Boundary Layer Transition, Part 3: Instability and Transition to Turbulence (outline of concepts) (Lecture held at Rhode-Saint-Genese, Belgium)
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