基于壁面压力分布的二元高超声速弯曲激波压缩进气道反设计与优化方法

推进技术 ›› 2013, Vol. 34 ›› Issue (12): 1601-1605.

• 气动热力学与总体技术 • 上一篇下一篇

基于壁面压力分布的二元高超声速弯曲激波压缩进气道反设计与优化方法

王磊,张堃元,金志光,张林,李永洲

南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016

发布日期:2021-08-15
作者简介:王磊(1987—),男,博士生,研究领域为高超声速进气道气动设计。E-mail:wang36288@gmail.com
基金资助:
国家自然科学基金(90916029；91116001)。

Reverse Design and Optimization of 2D Hypersonic Curved Shock Compression Inlet Based on Given Wall Pressure Distribution

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

Published:2021-08-15

摘要/Abstract

摘要： 为进一步提高高超声速进气道的性能,发展了通过指定压力分布规律来反设计整个二元进气道的方法,实现了气动参数可控的进气道内外压缩一体化设计,建立了基于Isight软件的进气道自动化设计分析和优化平台。初步的研究表明,使用此设计方法,能够得到综合性能优秀的进气道设计方案,该方案在来流马赫数6下喉道总压恢复系数为0.68,在来流马赫数4时流量系数达0.77。 

关键词: 高超声速进气道;弯曲激波压缩;气动反设计;多目标优化 

Abstract: In order to improve the performance of hypersonic inlet, a method of reverse designing two-dimensional hypersonic inlet according to specified wall pressure distribution was developed.An integrated designing method of inlet external and internal compression with controllable gas-dynamic parameters was achieved, and an automatic designing, simulation and optimization system of hypersonic inlet was created based on commercial software Isight. The preliminary study shows that inlet with good comprehensive performance could be obtained in this way. The optimized inlet system has total pressure recovery of 0.68at the throat section under Mach 6, and mass flow capture of 0.77under Mach 4.

Key words: Hypersonic inlet; Curved shock compression; Gas-dynamic reverse design; Multi-objective optimization

王磊,张堃元,金志光,张林,李永洲. 基于壁面压力分布的二元高超声速弯曲激波压缩进气道反设计与优化方法[J]. 推进技术, 2013, 34(12): 1601-1605.

WANG Lei, ZHANG Kun-yuan, JIN Zhi-guang, ZHANG Lin, LI Yong-zhou. Reverse Design and Optimization of 2D Hypersonic Curved Shock Compression Inlet Based on Given Wall Pressure Distribution[J]. Journal of Propulsion Technology, 2013, 34(12): 1601-1605.

参考文献

[1] Curran E T, Murthy S N B.Scramjet Propulsion, Progress in Astronautics and Aeronautics [M].Washington D C:AIAA Inc, 2000.
[2] 姜宗林.关于吸气式高超声速推进技术研究的思考[J].力学进展, 2009,9(4):398-405.
[3] 刘兴洲.中国超燃冲压发动机研究回顾[J].推进技术, 2008,9(4):385-395.(LIU Xing-zhou.Review of Scramjet Research in China[J].Journal of Propulsion Technology, 2008,9(4):385-395.)
[4] 范晓樯.高超声速进气道的设计、计算与实验研究[D].长沙:国防科学技术大学,2005.
[5] ZHANG Kun-yuan, Meier G E A.Using R.C.Method to Study Optimum Compression Surface Under Non-Uniform 2-D Supersonic Flow Condition[R].AIAA 94-1838.
[6] 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, 2004,5(3):226-229.(JIN Zhi-guang, ZHANG Kun-yuan.Concept of a Two-Dimensional Supersonic/Hypersonic Inlet with a Non-Conventional Compression Wall [J].Journal of Propulsion Technology, 2004,5(03):226-229.)
[7] 居燕.弯曲激波压缩面设计及试验研究[D].南京:南京航空航天大学, 2005.
[8] 潘瑾.超声/高超声速非均匀来流下曲面压缩系统研究[D].南京:南京航空航天大学, 2011.
[9] 南向军,张堃元,金志光,等.压升规律可控的高超声速内收缩进气道设计[J].航空动力学报,2011,6(3):518-523.
[10] WANG Lei, ZHANG Kun-yuan, NAN Xiang-jun, et al.Optimization and Experimental Investigation of 2-D Hypersonic Curved Shock [R].AIAA 2012-5959.
[11] 王磊,张堃元,向有志, 等.高超声速二元弯曲激波压缩面反设计方法的参数化研究[J].南京航空航天大学学报,2013,5(4):441-449.
[12] 李永洲,张堃元,南向军.基于马赫数分布规律可控概念的高超声速内收缩进气道设计[J].航空动力学报,2012,7(11):2484~2491.
[13] 张林,张堃元,王磊,等.基于壁面马赫数梯度的高超声速弯曲激波二维进气道数值研究[J].航空动力学报,2013,8(4):752-758.
[14] 张晓嘉,梁德旺,黄国平,等.二元高超声速进气道内压缩通道/隔离段曲面构型[J].推进技术,2008,9(1):49-53.(ZHANG Xiao-jia, LIANG De-wang, HUANG Guo-ping, et al.Curved Surface Structure of Internal Contraction Tunnel/Isolator of Two-Dimensional Hypersonic Inlet[J].Journal of Propulsion Technology, 2008,9(1):49-53.)
[15] 黎明,宋文艳,贺伟,等.高超声速二维混压式前体/进气道设计方法研究[J].航空动力学报,2004,9(4):459-465.
[16] 陈兵.空间推进算法及超燃冲压发动机部件优化设计研究 [D].北京:北京航空航天大学, 2006.
[17] 吴先宇.超燃冲压发动机一体化流道设计优化研究[D].长沙:国防科技大学, 2007.

基于壁面压力分布的二元高超声速弯曲激波压缩进气道反设计与优化方法

Reverse Design and Optimization of 2D Hypersonic Curved Shock Compression Inlet Based on Given Wall Pressure Distribution

PDF

可视化

被引次数

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价