航天推进技术研究院主办
[1]陈景昊,周树平,张文锋.不同攻角下高超声速二元进气道性能研究[J].火箭推进,2014,40(05):20-23.
CHEN Jing-hao,ZHOU Shu-ping,ZHANG Wen-feng.Performance study of hypersonic two-dimensional inlets with different attack angles[J].Journal of Rocket Propulsion,2014,40(05):20-23.
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CHEN Jing-hao,ZHOU Shu-ping,ZHANG Wen-feng.Performance study of hypersonic two-dimensional inlets with different attack angles[J].Journal of Rocket Propulsion,2014,40(05):20-23.
不同攻角下高超声速二元进气道性能研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
40
期数:
2014年05期
页码:
20-23
栏目:
研究与设计
出版日期:
2014-10-28
- Title:
- Performance study of hypersonic two-dimensional inlets with different attack angles
- Keywords:
- hypersonic inlet; internal compression section with multi-ramp surface; multi-ramp surface design
- 分类号:
- V235.21-34
- 文献标志码:
- A
- 摘要:
- 针对高超声速二维混压进气道，以最大总压恢复系数为目标，基于多楔面内收缩段设计原理，利用多楔角方法设计内收缩段长度和出口高度等。通过比较不同攻角下二元进气道总压恢复系数、流场及启动情况等多方面特性，验证了改变攻角对进气道启动特性改善的效果。
- Abstract:
- For two-dimensional mixed-compression hypersonic inlet, the internal compression section length and exit height were designed with the multi-ramp angle method to achieve the maximal recover coefficient according to the design theory of multi-wedge surface internal compression section. By comparing the total pressure recover coefficients, flow field and starting characteristics of two-dimensional inlets with different attack angles, the effect of changing attack angle on the improvement of inlet starting characteristics was validated.
参考文献/References:
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[3]张晓嘉, 梁德旺. 典型几何和流动参数对高超声速进气道性能的影响[J]. 南京航空航天大学学报, 2007, 39(6):765-770.
[4]张晓嘉, 梁德旺. 内压缩通道几何参数对高超声速进气道性能的影响[J]. 南京航空航天大学学报, 2005, 37(6):685-689.
[5]金志光, 张元. 宽马赫数范围高超声速进气道伸缩唇口式简单变几何方案研究[J].宇航学报, 2010, 31(5):1503- 1510.
[6]MROZINSKI D P, HAYES J R. Numerical and ex- perimental analysis of a hypersonic variable geometry inlet, AIAA-1999-899[R]. USA: AIAA, 1999.
[7]李航, 李博. 二元高超声速进气道的内压段设计[J]. 航空动力学报, 2013, 28(6): 96-102.
[8]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[J]. 航空动力学报, 2012, 27(11): 73-79.
[9]HENDERSON L K. Maximum total pressure recovery across a system of shock waves[J]. AIAA Journal, 1964, 2(6): 1138-1140.
[10]HEISER W H, PRATT D T, DELEY D H, et al. Hyper- sonic airbreathing propulsion[M]. Washington, D C: Ame- rican Institute of Aeronautics and Astronautics Inc,1994.
[11]SMART M K. Optimization of two-dimensional scramjet inlets[J]. Journal of Aircraft, 1999, 36(2): 430-433.
[12]SMART M K, TREXLER C A. Mach 4 performance of a fixed-geometry hypersonic inlet with rectangular-to- elliptical shape transition, AIAA 2003-0012[R]. USA: AIAA, 2003.
相似文献/References:
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LI Yongzhou,LIU Xiaowei,ZHANG Mengzheng,et al.Design of a two dimensional variable geometry
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备注/Memo
收稿日期：2014-04-22；修回日期：2014-05-29 基金项目：航空科学基金资助项目(2012ZC12001) 作者简介：陈景昊（1986—），男，助理工程师，研究领域为飞行器总体设计
更新日期/Last Update:
1900-01-01