高超弯曲激波二维进气道初步研究

张林; 张堃元; 王磊; 南向军; 向有志

高超弯曲激波二维进气道初步研究

基金项目: 国家自然科学基金(90916029)

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出版历程
- 收稿日期: 2010-12-15
- 修回日期: 2011-04-23
- 刊出日期: 2011-11-28

Preliminary study on hypersonic curved shock two-dimensional inlet

摘要

摘要: 研究了一种压升规律的曲面压缩面,设计了高超弯曲激波二维进气道,并用数值模拟手段对该进气道和同等条件下的常规高超二维三楔进气道、楔+等熵进气道的性能进行了比较.数值模拟表明:通过给定合理压缩面压升规律来设计压缩面并改善压缩面附面层稳定性是可行的,弯曲激波二维进气道的长度比同等条件下的常规二维三楔、楔+等熵进气道分别缩短12%和10%,并且对来流 Ma 变化不敏感,综合性能优势明显、应用前景大.
- 超燃冲压发动机进气道 /
- 二维高超声速进气道 /
- 压升规律 /
- 弯曲激波 /
- 数值仿真
Abstract: A type of curved compression surface with certain wall pressure distribution was investigated,and a hypersonic curved shock two-dimensional inlet was designed.The performance was compared through numerical simulation with normal hypersonic three-wedge and wedge-isentropic two-dimensional inlets under the same conditions.The result shows:the curved shock inlet with more stable boundary layer can be designed according a proper wall pressure distribution;the inlet can be shortened by 12% and 10%,respectively,as compared with three-wedge inlet and wedge-isentropic inlet,and is not very sensitive to the change of free stream Mach number;the new inlet has obvious superiority on the overall performance and bright prospect in the applications.
- scramjet inlet /
- two-dimensional hypersonic inlet /
- law of pressure rise /

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参考文献(12)

[1]	Samanich N E,Cubbison R W.A pivoting cowl and spike technique for efficient angle-of-attack operation of supersonic inlets .NACA RM E58G11a,1958.
[2]	Connors J F,Woollett R R.Performance characteristics of several types of axially symmetric nose inlets at Mach number 3.85 .NACA RM E52I15,1952.
[3]	Sorensen N E,Smeltzer D B.Study of two axisymmetric inlets for Mach 3.5 .AIAA 1976-0204,1976.
[4]	Mlder S,Szpiro J.Busemman inlet for hypersonic speeds[J].Journal of Spacecraft and Rockets,1966,3(8):1303-1304.
[5]	Smart M K.Design of three-dimensional hypersonic inlets with rectangular to elliptical shape transition .AIAA 98-0960,1998.
[6]	Billig F S.SCRAM:a supersonic combustion ramjet missile .AIAA Paper 93-2329,1993.
[7]	金志光,张堃元.二维非常规压缩型面超/高超声速进气道的设计概念[J].推进技术,2004,25(3):226-229. JIN Zhiguang,ZHANG Kunyuan.Concept of a two-dimensional supersonic/hypersonic inlet with a non-conventional compression wall[J].Journal of Propulsion Technology,2004,25(3):226-229(in Chinese).
[8]	居燕.弯曲激波压缩面设计及试验研究 .南京:南京航空航天大学 2005. JU Yan.Design of curved shock compression surface and experimental investigation . Nanjing:Nanjing University of Aeronautics and Astronautics,2005. (in Chinese)
[9]	潘瑾,张堃元,金志光.弯曲激波压缩型面的设计及数值分析[J].推进技术,2008,29(4):438-442. PAN Jin,ZHANG Kunyuan,JIN Zhiguang.Design and numerical inivestigation of curved shock compression surface[J].Journal of Propulsion Technology,2008,29(4):438-442.(in Chinese)
[10]	潘瑾,张堃元,王磊.几种超声速非常规压缩系统的研究[J].推进技术,2009,30(6):673-676. PAN Jin,ZHANG Kunyuan,WANG Lei.Study of several supersonic non-conventional compression surfaces[J].Journal of Propulsion Technology,2009,29(4):673-676.(in Chinese)
[11]	PAN Jin,ZHANG Kunyuan.Experimental and numerical investigation of a curved compression system designed on constant pressure gradient .AIAA 2009-5270,2009.
[12]	张堃元,居燕,杨国亮,等.曲面激波压缩和在高超声速进气道上的应用 //中国力学学会学术大会论文集.北京:中国力学学会,2007:80.