高超声速进气道自起动过程中流动非定常特性

doi:10.7527/S1000-6893.2015.0079

流体力学与飞行力学

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高超声速进气道自起动过程中流动非定常特性

王卫星^1,2, 郭荣伟¹

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016;
2. 中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室, 绵阳 621000

收稿日期:2014-11-26 修回日期:2015-03-23 出版日期:2015-10-15 发布日期:2015-10-27
通讯作者: 王卫星, Tel.: 025-84892200-2415 E-mail: wangweixing@nuaa.edu.cn E-mail:wangweixing@nuaa.edu.cn
作者简介:王卫星男, 博士, 讲师。主要研究方向: 高超声速进气道设计、流动机理。 Tel: 025-84892200-2415 E-mail: wangweixing@nuaa.edu.cn;郭荣伟男, 学士, 教授, 博士生导师。主要研究方向: 内流空气动力学、电磁隐身。 Tel: 025-84892444 E-mail: guoweifang@nuaa.edu.cn
基金资助:
高超声速冲压发动机技术重点实验室开放基金 (STS/MY-ZY-2012-002-5)

Unsteady flow characteristics of hypersonic inlet during self-starting

WANG Weixing^1,2, GUO Rongwei¹

1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2014-11-26 Revised:2015-03-23 Online:2015-10-15 Published:2015-10-27
Contact: 10.7527/S1000-6893.2015.0079 E-mail:wangweixing@nuaa.edu.cn
Supported by:
Open Fund of Science and Technology on Scramjet Laboratory (STS/MY-ZY-2012-002-5)

摘要/Abstract

摘要：

采用非定常数值仿真方法研究了进气道自起动过程中流动的非定常特性,分析了内压段构型对非定常流动特性的影响。研究结果表明:进气道自起动过程中流动特性受内压段构型与来流条件影响。内压段压缩面肩部曲率半径越大,内压段面积收缩越缓,越易出现流场振荡现象,流场振荡越剧烈;型面设计参数β≤33°,能够避免流场振荡现象出现。合理设计进气道内压段型面能够控制自起动过程中流动的非定常特性。自起动过程中,流场出现振荡时随着来流马赫数增大流动依次经历不振荡状态→振荡状态→不振荡状态→起动状态,且流场振荡频率逐渐下降;对于未发生流场振荡的进气道,随着来流马赫数增大进气道依次经历硬不起动状态→软不起动状态→起动状态。

关键词: 自起动, 非定常, 流场振荡, 高超声速进气道, 数值仿真

Abstract:

The unsteady flow characteristics of hypersonic inlet and the influence of the internal compression duct geometry on them during self-starting are studied with the unsteady numerical simulation. The results show that the unsteady flow characteristics are influenced by the internal compression duct geometry and the free stream condition. The curvature radius of the shoulder of internal compression surface is larger, the contraction rate of internal compression duct is slower, and the flow oscillation occurs easily with stronger oscillation intension. However, the flow oscillation disappears when the curvature radius of the shoulder is small enough (the geometry parameter β≤33°). If the flow oscillation occurs during inlet self-starting, the oscillation frequency decreases and the no oscillation, oscillation, no oscillation and started mode appears one by one with the increase of free stream Mach number. And for the case that the flow oscillation does not occur during self-starting, the inlet suffers the hard-unstarted mode, soft-unstarted mode and started mode in sequence with the free-stream Mach number increasing.

Key words: self-starting, unsteady, flow oscillation, hypersonic inlet, numerical simulation

中图分类号:

V211.3

王卫星, 郭荣伟. 高超声速进气道自起动过程中流动非定常特性[J]. 航空学报, 2015, 36(10): 3263-3274.

WANG Weixing, GUO Rongwei. Unsteady flow characteristics of hypersonic inlet during self-starting[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(10): 3263-3274.

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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

高超声速进气道自起动过程中流动非定常特性

Unsteady flow characteristics of hypersonic inlet during self-starting

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