基于马赫数分布可控曲面外/内锥形基准流场的前体/进气道一体化设计

doi:10.7527/S1000-6893.2014.0263

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基于马赫数分布可控曲面外/内锥形基准流场的前体/进气道一体化设计

李永洲, 张堃元

南京航空航天大学能源与动力学院, 南京 210016

收稿日期:2014-07-25 修回日期:2014-09-17 出版日期:2015-01-15 发布日期:2014-09-22
通讯作者: 张堃元,Tel.: 025-84892201-2100 E-mail: zkype@nuaa.edu.cn E-mail:zkype@nuaa.edu.cn
作者简介:李永洲男, 博士研究生。主要研究方向: 高超声速推进技术和内流气体动力学。 Tel: 025-84892240 E-mail: nuaa-2004@126.com;张堃元男, 硕士, 教授, 博士生导师。主要研究方向: 高超声速推进技术和内流气体动力学。 Tel: 025-84892201-2100 E-mail: zkype@nuaa.edu.cn
基金资助:
国家自然科学基金 (90916029, 91116001, 11102087)

Integrated design of forebody and inlet based on external and internal conical basic flow field with controlled Mach number distribution surface

LI Yongzhou, ZHANG Kunyuan

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

Received:2014-07-25 Revised:2014-09-17 Online:2015-01-15 Published:2014-09-22
Supported by:
National Natural Science Foundation of China (90916029, 91116001, 11102087)

摘要/Abstract

摘要：

提出了一种高超声速飞行器乘波前体的外锥形基准流场设计方法,在锥面马赫数分布规律给定的条件下,通过有旋特征线法实现反设计,提高了基准流场设计的灵活性。该基准流场通过锥形"下凹"弯曲激波和波后等熵压缩波系压缩气流,可以在较短的长度内完成高效压缩。基于反正切马赫数分布外锥形基准流场设计的乘波前体具有较高的容积率,乘波特性良好且出口均匀,设计点时有黏升阻比为1.89。另外,基于该乘波前体和马赫数分布可控的内收缩进气道给出了一种双乘波的前体与进气道一体化设计方案,实现了内外流分别独立乘波,充分发挥了乘波前体和内收缩进气道的各自优势。

关键词: 高超声速进气道, 乘波前体, 基准流场, 马赫数分布, 双乘波, 一体化设计

Abstract:

Design method of external conical basic flow field for hypersonic waverider forebody with controllable Mach number distribution surface is proposed to improve their flexibility in this paper. The basic flow field is designed reversely from assigned conical surface Mach number distribution utilizing the rotational method of characteristics. The characteristic of this basic flow field is that the incoming flow can be efficiently compressed by concave cone shock and isentropic compression waves within short length. With the basic flow field of antitangent Mach number distribution, the waverider forebody is designed with high volume ratio, good waverider characteristics and exit uniformity. On-design lift-drag ratio is 1.89 under viscous condition. Then, based on this waverider forebody and inward turning inlet with controllable Mach number distribution, a dual waverider configuration integrated with forebody and inlet is proposed which achieves the internal and external flows waverider respectively, maximizing their own advantages.

Key words: hypersonic inlets, waverider forebody, basic flow field, Mach number distribution, dual waverider, integrated design

中图分类号:

V231.3

李永洲, 张堃元. 基于马赫数分布可控曲面外/内锥形基准流场的前体/进气道一体化设计[J]. 航空学报, 2015, 36(1): 289-301.

LI Yongzhou, ZHANG Kunyuan. Integrated design of forebody and inlet based on external and internal conical basic flow field with controlled Mach number distribution surface[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(1): 289-301.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于马赫数分布可控曲面外/内锥形基准流场的前体/进气道一体化设计

Integrated design of forebody and inlet based on external and internal conical basic flow field with controlled Mach number distribution surface

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