内收缩比可控的二元高超声速变几何进气道研究

袁化成; 滕健; 郭荣伟

内收缩比可控的二元高超声速变几何进气道研究

南京航空航天大学能源与动力学院, 南京 210016

基金项目: 南京航空航天大学基本科研业务费专项科研项目(NS2010054); 高等学校博士学科点专项科研基金(20103218120009)

计量
- 文章访问数: 1919
- HTML浏览量: 80
- PDF量: 536
- 被引次数: 0
出版历程
- 收稿日期: 2011-11-03
- 刊出日期: 2012-11-28

Research on variable geometry technology of 2-D hypersonic inlet with contract ratio under controlling

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 提出了一种进气道内收缩比可控、包括唇口后退等几何动作的变几何进气道的设计思路,给出了具体的设计过程及影响因素.据此开展了二元高超声速定、变几何进气道气动方案设计,并进行了细致的数值模拟,给出了进气道气动性能参数随来流马赫数的变化规律,将定、变几何进气道气动性能进行了对比分析,结果显示:设计马赫数下,定、变几何进气道气动性能基本相同;非设计马赫数下,变几何进气道的流量系数明显高于定几何方案,且马赫数越低,两者相差越大.静压比、温升比、总压恢复系数及隔离段出口马赫数则相差不大.
- 高超声速推进系统 /
- 高超进气道 /
- 变几何 /
- 伸缩唇口 /
- 数值模拟
Abstract: Based on the two-dimensional(2-D)fixed hypersonic,a new concept of variable geometry hypersonic inlet that the tip moving back off to increase the mass capture ratio was presented.The flow in the hypersonic inlet was analyzed with two-dimensional numerical analyzer,and the inlet performance comparisons were made between the variable geometry hypersonic inlet and fixed inlet at different Mach numbers of inflow.The results indicate that the performance of the variable geometry inlet in the same as that of the fixed one at design Mach number,and the performance of the variable geometry inlet is better than that of the fixed inlet at non design point.All of them indicate that the variable geometry hypersonic inlet is satisfying.
- hypersonic propulsion system /
- hypersonic inlet /
- variable geometry /
- translating cowl /
- numerical simulation

HTML

参考文献(15)

[1]	William H H,David T P.Hypersonic air breathing propulsion[M].Washington, D C:AIAA Education Series,1994.
[2]	Van Wie D M,Kwok F T,Walsh R F.Starting characteristics of supersonic inlets [R].AIAA-96-2914,1996.
[3]	梁德旺,袁化成,张晓嘉,等.影响高超声速进气道起动能力的因素分析[J].宇航学报,2006,27(4):714-719. LIANG Dewang,YUAN Huacheng,ZHANG Xiaojia,et al.Research on the effects of start ability of hypersonic inlet[J].Journal of Astronautics,2006,27(4):714-719.(in Chinese)
[4]	袁化成,梁德旺.典型高超声速侧压式进气道的不起动特性分析[J].南京航空航天大学学报,2004,36(6):683-687. YUAN Huacheng,LIANG Dewang.Analysis of characteristics of unstart performance for a hypersonic side-wall inlet model[J].Journal of Nanjing University of Aeronautics & Astronautics,2004,36(6):683-687.(in Chinese)
[5]	Bouchez M,Falempin F.Air breathing space launcher interest of a fully variable geometry propulsion system status 1999 [R].AIAA-99-2376,1999.
[6]	Mrozinski D P,Hayes J R.Numerical and experimental analysis of a hypersonic variable geometry inlet [R].AIAA-99-0899,1999.
[7]	Huebner L D,Rock K E,Ruf E G,et al.Hyper-X flight engine ground testing for X-43 flight risk reduction [R].AIAA-2001-1809,2001.
[8]	Falempin F,Wendling E,Goldfeld M,et al.Experimental investigation of starting process for a variable geometry air inlet operating from Mach 2 to Mach 8 [R].AIAA-2006-4513,2006.
[9]	Kojima T,Taguchi T H,Aoki K,et al.Development study of the air-intake of the ATREX engine [R].AIAA-2003-7042,2003.
[10]	Keiichi O,Hideyuki T,Takayuki K,et al.Numerical analysis of variable intake and nozzle for hypersonic engine [R].AIAA-2003-7069,2003.
[11]	严红明,钟兢军,杨凌,等.组合发动机可调进气道气动性能[J].航空动力学报,2011,26(2):458-467. YAN Hongming,ZHONG Jingjun,YANG Ling,et al.Aerodynamic characteristics research on variable geometry inlet of combined cycle engine[J].Journal of Aerospace Power,2011,26(2):458-467.(in Chinese)
[12]	金志光,张堃元.宽马赫数范围高超声速进气道伸缩唇口式变几何方案[J].宇航学报,2010,31(5):1503-1510. JIN Zhiguang,ZHANG Kunyuan.A variable geometry scramjet inlet with a translating cowl operating in a large Mach number range[J].Journal of Astronautics,2010,31(5):1503-1510.(in Chinese)
[13]	袁化成,刘大,梁德旺,等.变唇口对高超声速进气道性能的影响新疆:第二届全国冲压发动机会议,2007.
[14]	袁化成.矩形截面高超声速变几何进气道设计方法及气动特性研究 [D].南京:南京航空航天大学,2008. YUAN Huacheng.Designing methodology and flow characteristic of hypersonic variable geometry inlet with rectangular section [D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[15]	袁化成,郭荣伟.矩形截面高超声速进气道气动设计及实验验证[J].南京航空航天大学学报,2009,41(4):423-428. YUAN Huacheng,GUO Rongwei.Design and experimental verification of hypersonic inlet with rectangular section[J].Journal of Nanjing University of Aeronautics and Astronautics,2009,41(4):423-428.(in Chinese)