二元高超声速进气道激波振荡特性实验

推进技术 ›› 2012, Vol. 33 ›› Issue (5): 676-682.

二元高超声速进气道激波振荡特性实验

李祝飞,高文智,李鹏,姜宏亮,杨基明

中国科学技术大学,安徽合肥 230027;中国科学技术大学,安徽合肥 230027;中国科学技术大学,安徽合肥 230027;中国科学技术大学,安徽合肥 230027;中国科学技术大学,安徽合肥 230027

发布日期:2021-08-15
作者简介:李祝飞(1986—),男,博士生,研究领域为高超声速进气道。 E-mail:lizhufei@mail.ustc.edu.cn
基金资助:
国家自然科学基金(11132010)。

Experimental Investigation on the Shock Wave Oscillation Behaviors in a Two-Dimensional Hypersonic Inlet Flow

University of Science and Technology of China, Hefei 230027, China;University of Science and Technology of China, Hefei 230027, China;University of Science and Technology of China, Hefei 230027, China;University of Science and Technology of China, Hefei 230027, China;University of Science and Technology of China, Hefei 230027, China

Published:2021-08-15

摘要/Abstract

摘要： 通过在进气道/隔离段模型出口附近设置固定的堵塞楔块提高反压,并采用高速纹影拍摄同步壁面压强测量的手段,在马赫数5.9的激波风洞中研究了二元高超声速进气道在不同堵塞度下的流动特征。研究结果表明,在较低的堵塞度下,进气道仍然能够保持起动状态,而在较高的堵塞度下,进气道出现激波振荡。上游产生的压缩波/激波在节流段的反射是出现激波振荡的重要原因之一。随着堵塞度的增加,激波振荡的频率有所升高。

关键词: 激波风洞; 高超声速进气道; 激波振荡

Abstract: A two-dimensional hypersonic inlet which exhibits self-starting characteristics was tested with different exit throttling ratios in shock tunnel at a freestream Mach number of 5.9 by applying simultaneously high speed schlieren imaging and surface pressure measurements. Results indicate that the backpressure generated from the throttling device can be tolerated and the inlet can maintain starting mode at low throttling ratios. Shock wave oscillations were observed and discussed in details when the inlet was operated at high exit throttling ratios. The upstream propagating normal shock in the duct during oscillation is related to the compression waves/ shock waves that reflect at the throttling section. The oscillation frequency increases with increasing exit throttling ratio.

Key words: Shock tunnel; Hypersonic inlet; Shock wave oscillation

李祝飞,高文智,李鹏,姜宏亮,杨基明. 二元高超声速进气道激波振荡特性实验[J]. 推进技术, 2012, 33(5): 676-682.

参考文献

[2] Ferri A, Nucci L M.The Origin of Aerodynamic Instability of Supersonic Inlets at Subcritical Conditions [R]. NACA RM L50K0,1.
[3] Dailey C L.Supersonic Diffuser Instability [D].Pasadena:Ph.D.Thesis, California Inst.of Technology, 1954.
[4] Lu P J, Jain L T.Numerical Investigation of Inlet Buzz Flow [J].Journal of Propulsion and Power, 8,4(1):90-100.
[5] Trapier S, Duveau P, Deck S.Experimental Study of Supersonic Inlet Buzz [J].AIAA Journal, 6,4(10):2354-2365.
[6] Lee H J, Lee B J, Kim S D, et al.Flow Characteristics of Small-Sized Supersonic Inlets [J].Journal of Propulsion and Power, 1,7(2):306-318.
[7] 刘占生, 张云峰, 田新.冲压发动机超声速进气道流动自激振荡研究 [J]．航空动力学报, 8,3(9):1595-1602.
[8] 孟宇鹏, 朱守梅, 闫晓娜.出口封闭的冲压发动机进气道激波振荡现象 [J].推进技术, 1,2(5):606-610.(MENG Yu-peng,ZHU Shou-mei,YAN Xiao-na.Shock Wave Oscillation for Outlet-Closed Ramjet Inlet[J].Journal of Propulsion Technology, 1,2(5):606-610.)
[9] Tan H J, Sun S, Yin Z L.Oscillatory Flows of Rectangular Hypersonic Inlet Unstart Caused by Downstream Mass-Flow Choking [J].Journal of Propulsion and Power, 9,5(1):138-147.
[10] 谢旅荣, 郭荣伟.一种高超声速二元混压式进气道的研究[J].航空学报, 9,0(12):2288-2294.
[11] Haberle J, Gulhan A.Investigation of Two-Dimensional Scramiet Inlet Flowfield at Mach 7 [J].Journal of Propulsion and Power, 8,4(3):446-459.
[12] Fischer C, Olivier H.Experimental Investigation of the Shock Train in an Isolator of a Scramjet Inlet [R].AIAA 2011-2220.
[13] Wagner J L, Yuceil K B, Valdivia A, et al.Experimental Investigation of Unstart in an Inlet/Isolator Model in Mach 5 Flow [J].AIAA Journal, 9,7(6):1528-1542.
[14] 余安远, 杨大伟, 张小庆, 等.高超声速前体进气道动态特性研究 [C].哈尔滨:中国力学学会学术大会,2011.
[15] 李祝飞, 黄舶, 贾立超, 等.激波风洞中高超声速进气道起动问题实验研究 [C].无锡:第三届高超声速科技学术会议,2010.
[16] Li Z, Huang B, Yang J.A Novel Test of Starting Characteristics of Hypersonic Inlets in Shock Tunnel [R].AIAA 2011-2308.
[17] 陈强.激波管流动的理论和实验技术[M].合肥:中国科学技术大学, 1975.