Numerical Research for Regularity of Wedge Shock Wave with Surface MHD Aerodynamic Actuation

Journal of Propulsion Technology ›› 2017, Vol. 38 ›› Issue (11): 2456-2462.

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Numerical Research for Regularity of Wedge Shock Wave with Surface MHD Aerodynamic Actuation

Science and Technology on Plasma Dynamics Laboratory，Air Force Engineering University，Xi’an 710038，China,Science and Technology on Plasma Dynamics Laboratory，Air Force Engineering University，Xi’an 710038，China,Science and Technology on Plasma Dynamics Laboratory，Air Force Engineering University，Xi’an 710038，China; Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China,Science and Technology on Plasma Dynamics Laboratory，Air Force Engineering University，Xi’an 710038，China,Science and Technology on Plasma Dynamics Laboratory，Air Force Engineering University，Xi’an 710038，China and Science and Technology on Plasma Dynamics Laboratory，Air Force Engineering University，Xi’an 710038，China

Published:2021-08-15

表面磁流体气动激励控制楔面激波规律数值研究

王宇天¹,张百灵¹,李益文^1,2,段成铎¹,庄重¹,张磊¹

空军工程大学等离子体动力学重点实验室，陕西西安 710038,空军工程大学等离子体动力学重点实验室，陕西西安 710038,空军工程大学等离子体动力学重点实验室，陕西西安 710038; 西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072,空军工程大学等离子体动力学重点实验室，陕西西安 710038,空军工程大学等离子体动力学重点实验室，陕西西安 710038,空军工程大学等离子体动力学重点实验室，陕西西安 710038

作者简介:王宇天，男，硕士生，研究领域为高超声速飞行磁流体动力技术。
基金资助:
国家自然科学基金(11372352；51306207)。

Abstract

Abstract: The paper is devoted to the scientific problem of control of hypersonic inlet shockwave at off-design state based on surface MHD aerodynamic actuation. The MHD kinetics model is established by a combination of Navier-Stokes equations and Ohm’s law，and the electromagnetism interaction is simplified as the source terms of Navier-Stokes based on phenomenology and assumption of low magnetic Reynolds number，meanwhile，the Hall effect is taken into consideration which results from electron cyclotron effect in low pressure and magnetic field intensity. The reasonability of the model is verified in contrast with experiment shockwave schlieren image，and the regularity of location and width of actuation region，magnetic field intensity，conductivity，energy conversion efficiency of MHD effect on the wedge shockwave is investigated by the model. The results show that the surface MHD aerodynamic actuation includes Joule heat and Lorentz force effects，when discharge power density is 3.8×109kW/m3 and magnetic field intensity is 0.34T，the MHD acceleration/deceleration actuation can make the shockwave 6mm and 10mm ahead respectively. When magnetic field intensity is low，the front-back ratio of pressure and magnetic field intensity increased as the result of leading role of the Joule heat. According to the regularity of actuation parameters，the actuator should be arranged closed to tip of the wedge，magnetic field intensity should be enhanced，conductivity should be increased by improving the plasma source technology，and width of actuation region should be increased appropriately.

Key words: Magnetohydrodynamic(MHD)；Shockwave；Flow control；Surface discharge；Magnetic field

摘要： 针对表面磁流体(MHD)气动激励对高超声速进气道在非设计状态下激波控制问题，从唯象学的角度出发，基于低磁雷诺数假设，将电磁作用简化为Navier-Stokes方程组中的源项处理，同时考虑到低气压、低磁场环境下电子回旋效应引起的Hall效应，并联立Ohm定律，建立磁流体动力学模型，通过与实验纹影对比验证了模型的合理性，并利用该模型研究了表面MHD加/减速激励作用位置与宽度、磁场强度、电导率和能量转化率等参数对楔面激波的影响规律。结果表明:表面MHD气动激励包括焦耳热与洛伦兹力作用，当放电功率密度为3.8×109kW/m3，磁场强度为0.34T时，MHD加/减速激励分别使激波位置前移6mm与10mm；而磁场强度较低时，由于焦耳热的主导作用，将会出现激波前后压力比增大，激波强度增加等负面效应；根据激励参数的影响规律，激励器电极应靠近尖端布置，增大磁场强度，并改善等离子体源以提高气体电导率，同时适当增大激励区域宽度。

关键词: 磁流体；激波；流动控制；表面放电；磁场

WANG Yu-tian¹,ZHANG Bai-ling¹,LI Yi-wen^1,2,DUAN Cheng-duo¹,ZHUANG Zhong¹,ZHANG Lei¹. Numerical Research for Regularity of Wedge Shock Wave with Surface MHD Aerodynamic Actuation[J]. Journal of Propulsion Technology, 2017, 38(11): 2456-2462.

王宇天,张百灵,李益文,段成铎,庄重,张磊. 表面磁流体气动激励控制楔面激波规律数值研究[J]. 推进技术, 2017, 38(11): 2456-2462.

References

[1] VanWie D M, Nedungadi A. Plasma Aerodynamic Flow Control for Hypersonic Inlets[R]. AIAA 2004-4129.
[2] Bityurin V A, Bocharov A N, Lineberry J. MHD Flow Control in Hypersonic Flight[R]. AIAA 2005-3225.
[3] Sheikin E G, Kuranov A L. MHD Control in Hypersonic Aircraft[R]. AIAA 2005-1335.
[4] 吴云, 李应红. 等离子体流动控制与点火助燃研究进展[J]. 高电压技术, 2014, 40(7): 2024-2038.
[5] Bobashev S V, Erofeev A V, Lapushkina T A, et al. Experiments on MHD Control of Attached Shocks in Diffuser[R]. AIAA 2003-169.
[6] Shneider M N, Macheret S O, Miles R B. Nonequilibrium Magnetohydrodynamic Control of Scramjet Inlets[R]. AIAA 2002-2251.
[7] Macheret S O, Shneider M N, Miles R B. Scramjet Inlet Control by Off-Body Energy Addition: a Virtual Cowl[R]. AIAA 2003-32.
[8] 郑小梅, 吕浩宇, 徐大军, 等. MHD加速器模式磁控进气道的优化设计[J]. 航空学报, 2010, 31(2): 223-230.
[9] 郑小梅, 吕浩宇, 徐大军, 等. 二维超燃冲压发动机磁控进气道的数值模拟[J]. 推进技术, 2010, 31(1): 13-17. (ZHENG Xiao-mei, LV Hao-yu, XU Da-jun, et al. Numerical Simulation of a Two-Dimensional Scramjet MHD Controlled Inlet[J]. Journal of Propulsion Technology, 2010, 31(1): 13-17.)
[10] 郑小梅, 徐大军, 蔡国飚. 磁控进气道二维性能计算[J]. 航空动力学报, 2009, 24(3): 581-587.
[11] 吕浩宇, 李椿萱. 三维非理想低磁雷诺数磁流体流动的数值模拟[J]. 中国科学E辑:技术科学, 2009, 39(11): 3690-3697.
[12] 田正雨, 张康平, 潘沙, 等. 磁流体动力学斜激波控制数值模拟分析[J]. 力学季刊, 2008, 29(1): 72-77.
[13] 苏纬仪, 陈立红, 张新宇. MHD控制激波诱导湍流边界层分离的机理分析[J]. 推进技术, 2010, 31(1): 18-23. (SU Wei-yi, CHEN Li-hong, ZHANG Xin-yu.Investigation of Magnetohydrodynamic Control on Boundary Layer Separation Induced by Shock Wave[J]. Journal of Propulsion Technology, 2010, 31(1): 18-23.)
[14] 苏纬仪, 张新宇, 张堃元. 洛仑兹力控制高超声速进气道边界层分离的数值模拟[J]. 推进技术, 2011, 32(1): 36-41. (SU Wei-yi, ZHANG Xin-yu, ZHANG Kun-yuan. Numerical Investigation of Lorentz Force Control on Hypersonic Inlet Boundary Layer Separation[J]. Journal of Propulsion Technology, 2011, 32(1): 36-41.)
[15] Leonov S B, Yarantsev D A. Near-Surface Electrical Discharge in Supersonic Airflow: Properties and Flow Control[J]. Journal of Propulsion and Power, 2008, 24(6): 1168-1181.
[16] Leonov S B, Firsov A A, Yarantsev D A, et al. Flow Control in Model Supersonic Inlet by Electrical Discharge[R]. AIAA 2009-7367.
[17] Leonov S B, Firsov A A, Yarantsev D A, et al. Plasma Effect on Shocks Configuration in Compression Ramp[R]. AIAA 2011-2362.
[18] Falempin F, Firsov A A, Yarantsev D A, et al. Plasma Control of Shock Wave Configuration in Off-Design Mode of M=2 Inlet[J]. Experiments in Fluids, 2015, 56(3): 1-10.
[19] Shang J S. Surface Direct Current Discharge for Hypersonic Flow Control[J]. Journal of Spacecraft and Rockets, 2008, 45(6): 1213-1222.
[20] Shang J S, Kimmel R L, Menart J, et al. Hypersonic Flow Control Using Surface Plasma Actuator[J]. Journal of Propulsion and Power, 2008, 24(5): 923-934.
[21] Kimmel R L, Hayes J R, Crafton J W, et al. Surface Discharges for High-Speed Boundary Layer Control[R].AIAA 2006-710.
[22] Watanabe Y, Suzuki Kojiro. Aerodynamic Control Effect of Surface DC Plasma Discharge at Mach-7 Hypersonic Flow[R]. AIAA 2015-2342.
[23] Wang J, Li Y H, Cheng B Q, et al. Effects of Plasma Aerodynamic Actuation on Oblique Shock Wave in a Cold Supersonic Flow[J]. Journal of Physics D: Applied Physics, 2009, 42(16).
[24] Wang J, Li Y H, Fei X. Investigation on Oblique Shock Wave Control by Arc Discharge Plasma in Supersonic Airflow[J]. Journal of Applied Physics, 2009, 106(7).
[25] Yan H. Near-Surface Discharge in Supersonic Inlet Control[R]. AIAA 2013-0530.
[26] 严红, 王松. 热激励在超声速进气道内对激波诱导的边界层分离的控制机理[J]. 空气动力学学报, 2014, 32(6): 806-813.
[27] 程钰锋, 聂万胜. 电弧放电等离子体诱导激波的计算[J]. 计算物理, 2012, 29(2): 213-220.
[28] 程钰锋, 聂万胜, 李国强. 等离子体气动激励机理数值研究[J]. 物理学报, 2012, 61(6).
[29] 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[J]. 力学学报, 2010, 42(4):782-788.
[30] Capitelli M, Colonna G, Gorse C, et al. Transport Properties of High Temperature Air in Local Thermodynamic Equilibrium[J]. The European Physical Journal D, 2000, 11(2): 279-289.
[31] Li Y H, Wu Y, Liang H, et al. The Mechanism of Plasma Shock Flow Control for Enhancing Flow Separation Control Capability[J]. Chinese Science Bull, 2010, 55(31): 3060-3068.
[32] Nishihara M, William Rich J, Lempert W R, et al. Low-Temperature M=3 Flow Deceleration by Lorentz Force[J]. Physics of Fluids, 2006, 18(8).
[33] Flitti A, Pancheshnyi S. Gas Heating in Fast Pulsed Discharges in N2-O₂ Mixtures[J]. The European Physical Journal Applied Physics, 2009, 45(2).
[34] Popov N A. Investigation of the Mechanism for Rapid Heating of Nitrogen and Air in Gas Discharges[J]. Low-Temperature Plasma, 2001, 27(10): 940-950.
[35] Poggie J, Adamovich I, Bisek N, et al. Numerical Simulation of Nanosecond-Pulse Electrical Discharges[J]. Plasma Sources Science and Technology, 2013, 22(1).(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2016-06-28；修订日期:2016-09-29。基金项目:国家自然科学基金(11372352；51306207)。作者简介:王宇天,男,硕士生,研究领域为高超声速飞行磁流体动力技术。E-mail: 3147526498@qq.com

Numerical Research for Regularity of Wedge Shock Wave with Surface MHD Aerodynamic Actuation

表面磁流体气动激励控制楔面激波规律数值研究

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