高超声速二元变几何进气道气动方案设计与调节规律研究
收稿日期: 2012-05-29
修回日期: 2012-09-20
网络出版日期: 2013-04-23
基金资助
国家自然科学基金(11102086)
Design and Regulation of Two-dimensional Variable Geometry Hypersonic Inlets
Received date: 2012-05-29
Revised date: 2012-09-20
Online published: 2013-04-23
Supported by
National Natural Science Foundation of China (11102086)
金志光 , 张堃元 , 陈卫明 , 刘媛 . 高超声速二元变几何进气道气动方案设计与调节规律研究[J]. 航空学报, 2013 , 34(4) : 779 -786 . DOI: 10.7527/S1000-6893.2013.0137
A variable geometry inlet with a rotating cowl operating in a large Mach number range with large angles of attack is studied through numerical simulation, which yields a design method of the baseline variable geometry inlet with high performance and a law of performance variation and regulation under different conditions. The result shows that: the variable geometry inlet with curved cowl has better performance and flow field structure in the large Mach number range. The variable geometry inlet designed at Mach number Ma=6.0 with a rotating cowl can realize self-start at Ma=4.0 without the boundary layer diverter, and the lowest Mach number of self-start is Ma=3.5. The cowl can maintain the normal working of the inlet by rotating properly to control the average Mach number of the throat at low incoming Mach numbers with large angles of attack.
[1] van Wie D M, Kwok F T, Walsh R F. Starting characteristics of supersonic inlets. AIAA-1996-2914, 1996.
[2] Bouchez M, Falempin F. Airbreathing space launcher interest of a fully variable geometry propulsion system status. AIAA-1999-2376, 1999.
[3] Huebner L D, Rock K E, Ruf E G, et al. Hyper-X flight engine ground testing for X-43 flight risk reduction. AIAA-2001-1809, 2001.
[4] 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. AIAA-2006-4513, 2006.
[5] Zhang H J, Liang D W, Guo R W. Study of flow characteristics for a variable geometry inlet on combined engine. Journal of Aerospace Power, 2009, 24(10): 2201-2207. (in Chinese) 张华军, 梁德旺, 郭荣伟. 一种组合发动机变几何进气道流场特性研究. 航空动力学报, 2009, 24(10): 2201-2207.
[6] Liu X W, He G Q, Liu P J. Investigation of a RBCC 2D variable-geometry inlet scheme. Journal of Solid Rocket Technology, 2010, 33(4): 409-418. (in Chinese) 刘晓伟, 何国强, 刘佩进. 一种RBCC二元进气道变几何方案研究. 固体火箭技术, 2010, 33(4): 409-418.
[7] Mrozinski D P, Hayes J R. Numerical and experimental analysis of a hypersonic variable geometry inlet. AIAA-1999-899, 1999.
[8] Jin Z G, Zhang K Y. Concept of a varied geometry scramjet inlet with rotatable cowl. Journal of Propulsion Technology, 2008, 29(1): 43-48. (in Chinese) 金志光, 张堃元. 高超侧压式进气道简单唇口调节方案设计. 推进技术, 2008, 29(1): 43-48.
[9] Wu J Q, Zhang K Y. Dynamic investigation on hypersonic sidewall compression inlets with cowl valve during the process of transition. Journal of Aerospace Power, 2009, 24(2): 296-301. (in Chinese) 吴俊琦, 张堃元.带唇口封气活门的高超侧压进气道过渡态工况气动性能. 航空动力学报, 2009, 24(2): 296-301.
[10] Pan J, Zhang K Y. Self-starting characteristics for sidewall-compression inlet with variable internal contraction ratio. Journal of Propulsion Technology, 2007, 28(3): 278-281. (in Chinese) 潘瑾, 张堃元. 可变内收缩比侧压式进气道自起动性能. 推进技术, 2007, 28(3): 278-281.
[11] Pan J, Zhang K Y. Study on back pressure and self-starting characteristics for sidewall-compression inlet with variable internal contraction ratio by moving cowl. Journal of Aerospace Power, 2009, 24(1): 104-109. (in Chinese) 潘瑾, 张堃元. 移动唇口变收缩比侧压式进气道反压特性和自起动性能. 航空动力学报, 2009, 24(1): 104-109.
[12] Chen Q H, Zhang K Y. The primary investigation on variable throat and top wall of sidewall compression inlet. Nanjing: College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, 2006.(in Chinese) 陈秋华, 张堃元. 喉道顶板可调侧压式进气道初步研究. 南京: 南京航空航天大学能源与动力学院, 2006.
[13] Wang Y, Fan X Q, Liang J H, et al. Experimental investigation on the starting characteristics of a hypersonic inlet with moving entrance door. Journal of Aerospace Power, 2008, 23(6): 1014-1018. (in Chinese) 王翼, 范晓墙, 梁剑寒, 等. 开启式高超声速进气道启动性能试验.航空动力学报, 2008, 23(6): 1014-1018.
[14] Jin Z G, Zhang K Y. A variable geometry scramjet inlet with a translating cowl operating in a large Mach number range. Journal of Astronautics, 2010, 31(5): 1503-1510. (in Chinese) 金志光, 张堃元.宽马赫数范围高超声速进气道伸缩唇口简单变几何方案研究.宇航学报, 2010, 31(5): 1503-1510.
[15] Jin Z G, Zhang K Y. Investigation of a variable geometry scramjet inlet with a rotating cowl operating in a large Mach number range. Journal of Aerospace Power, 2010, 25(7): 1553-1560.(in Chinese) 金志光, 张堃元. 宽马赫数范围高超声速进气道转动唇口变几何方案研究. 航空动力学报, 2010, 25(7): 1553-1560.
/
| 〈 |
|
〉 |
CJA