带凹腔钝头体第IV类激波干扰特性研究

推进技术 ›› 2016, Vol. 37 ›› Issue (1): 1-7.

• 总体与系统 • 下一篇

带凹腔钝头体第IV类激波干扰特性研究

肖丰收,李祝飞,朱雨建,杨基明

中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027

发布日期:2021-08-15
作者简介:肖丰收，男，博士生，研究领域为高超声速空气动力学。
基金资助:
国家自然科学基金(11132010，11402263)。

Effects of Forward-Facing Cavity on Behaviors of Type IV

Department of Modem Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modem Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modem Mechanics，University of Science and Technology of China，Hefei 230027，China and Department of Modem Mechanics，University of Science and Technology of China，Hefei 230027，China

Published:2021-08-15

摘要/Abstract

摘要： 采用激波风洞实验与数值模拟相结合的方法，对高超声速带凹腔钝头体的第IV类激波干扰非定常振荡特性进行了考察和分析。结果表明，随着入射激波与弓形激波相对位置的不同，第IV类激波干扰既可能出现稳定的波系干扰结构，也可能出现较为剧烈的非定常振荡现象。在实验条件下，观察到了高频前后振荡和低频上下振荡两种不同的振荡模式。数值模拟结果与实验吻合较好，超声速射流与凹腔的耦合作用在振荡过程中起到了关键作用。

关键词: 高超声速流动；激波/激波干扰；带凹腔钝头体；振荡模式

Abstract: The effects of blunt body with a forward-facing cavity on the unsteady behaviors of hypersonic type IV shock interaction were experimentally and numerically investigated . The results show that type IV shock interaction can be either steady or unsteady depending on the location of the oblique impinging shock/bow shock intersection point. Under the conditions within the current work，two different oscillation modes，namely high frequency forward-backward oscillation and low frequency up-down oscillation modes were observed. The numerical results agree fairly well with those of the experiments. The interaction between the supersonic jet and the forward-facing cavity plays a key role in the shock wave oscillations.

Key words: Hypersonic flow；Shock/Shock interaction；Blunt body with a forward-facing cavity；Oscillation modes

肖丰收,李祝飞,朱雨建,杨基明. 带凹腔钝头体第IV类激波干扰特性研究[J]. 推进技术, 2016, 37(1): 1-7.

XIAO Feng-shou,LI Zhu-fei,ZHU Yu-jian,YANG Ji-ming. Effects of Forward-Facing Cavity on Behaviors of Type IV[J]. Journal of Propulsion Technology, 2016, 37(1): 1-7.

参考文献

[1] Edney B. Anomalous Heat Transfer and Pressure Distributions on Blunt Bodies at Hypersonic Speeds in the Presence of an Impinging Shock[R]. Sweden: Aeronautical Research Institute of Sweden, FFA Report No.115, 1968.
[2] Wieting A R, Holden M S. Experimental Shock-Wave Interference Heating on a Cylinder at Mach 6 and 8[J]. AIAA Journal, 1989, 27(11): 1557～1565.
[3] Holden M S, Wieting A R, Moselle J R, et al. Studies of Aerothermal Loads Generated in Regions of Shock/Shock Interaction in Hypersonic Flow[R]. AIAA 88-0477.
[4] Gaitonde D, Shang J S. On the Structure of an Unsteady Type IV Interaction at Mach 8[J]. Computers & Fluids, 1995, 24(4): 469～485.
[5] Zhong X. Application of Essentially Nonoscillatory Shemes to Unsteady Hypersonic Shock-Shock Interference Heating Problems[J]. AIAA Journal, 1994, 32(8): 1606～ 1616.
[6] Chu Y B, Lu X Y. Characteristics of Unsteady Type IV Shock/Shock Interaction[J]. Shock Waves, 2012, 22(3): 225～ 235.
[7] Aso S, Hayashi K, Mizoguchi M. A Study on Aerodynamic Heating Reduction due to Opposing Jet in Hypersonic Flow[R]. AIAA 2002-0646.
[8] 陆海波, 刘伟强. 迎风凹腔与逆向喷流组合热防护系统冷却效果研究[J]. 物理学报, 2012, 61(6), 064703.
[9] 王兴, 裴曦, 陈志敏, 等. 超声速逆向喷流的减阻与降热[J]. 推进技术, 2010, 31(3): 261-264. (WANG Xing, PEI Xi, CHEN Zhi-min, et al. Supersonic with Counter-Flowing Jets on Drag and Heat-Transfer Reduction[J]. Journal of Propulsion Technology, 2010, 31(3):261-264.)
[10] Engblom W A, Yuceil B, Goldstein D B, et al. Experimental and Numerical Study of Hypersonic Forward-Facing Cavity Flow[J]. Journal of Spacecraft and Rockets, 1996, 33(3): 353-359.
[11] Saravanan S, Jagadeesh G, Reddy K P J. Investigation of Missile-Shaped Body with Forward-Facing Cavity at Mach 8[J]. Journal of Spacecraft and Rockets, 2009, 46(3): 577-591.
[12] Prabhu R K, Wieting A R, Thareja R R. Computational Studies of a Fluid Spike as a Leading Edge Protection Device for Shock-Shock Interference Heating[R]. AIAA 91-1734.
[13] Albertson C W, Venkat V S. Shock Interaction Control for Scramjet Cowl Leading Edges[R]. AIAA 2005-3289.
[14] Kolly J M. An Investigation of Aerothermal Loads Generated in Regions of Hypersonic Shock Interference Flows [D]. New York: State University of New York at Buffalo, 1996.
[15] Sanderson S R. Shock Wave Interaction in Hypervelocity Flow[D]. California: California Institute of Technology, 1995.
[16] Sun M, Takayama K. Conservative Smoothing on an Adaptive Quadrilateral Grid[J]. Journal of Computational Physics, 1999, 150(1): 143～180.
[17] Boldyrev S M, Borovoy V Y, Chinilov A Y, et al. A Thorough Experimental Investigation of Shock/Shock Interferences in High Mach Number Flows[J]. Aerospace Science and Technology, 2001, 5(3): 167～178.
[18] 阎超, 涂正光, 于晓红, 等. 激波碰撞干扰流动非定常效应的数值研究[J]. 北京航空航天大学学报, 2003, 29(3): 214-217. (编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2014-10-09；修订日期:2014-10-28。基金项目:国家自然科学基金(11132010,11402263)。作者简介:肖丰收,男,博士生,研究领域为高超声速空气动力学。E-mail: xfshou@mail.ustc.edu.cn

带凹腔钝头体第IV类激波干扰特性研究

Effects of Forward-Facing Cavity on Behaviors of Type IV

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