咽式进气道设计工况下性能初步分析

辜天来; 付磊; 张帅; 郑耀

doi:10.13224/j.cnki.jasp.2014.09.008

咽式进气道设计工况下性能初步分析

doi: 10.13224/j.cnki.jasp.2014.09.008

浙江大学航空航天学院, 杭州 310027

基金项目:

浙江省自然科学基金（Y13E060006）

详细信息

作者简介:
辜天来（1990-），男，湖北孝感人，博士生，主要从事高超声速飞行器设计研究.

通讯作者:
张帅（1977-），男，江苏南京人，副教授，博士，主要从事高超声速飞行器设计研究.E-mail：shuaizhang@zju.edu.cn

中图分类号: V235.213
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出版历程
- 收稿日期: 2013-06-03
- 刊出日期: 2014-09-28

Preliminary analysis of jaws inlet performance under design conditions

School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China

摘要

摘要: 介绍了三维内收缩高超声速咽式进气道的设计方法，开发了相应的设计程序.在高度为30 km，设计马赫数为5和攻角为0°工况下进行设计，使用CFD模拟技术，对设计方法和程序进行了验证.最后采用设计程序，考虑咽式进气道的设计参数，即流线追踪出口形状、基准流场压缩角和设计马赫数等，对比分析了其对咽式进气道设计工况下几何与气动性能的影响.结果表明：矩形出口宽高比接近2时，总长、润周面积等几何性能相比较小宽高比时更好.初步设计可以将压缩角配置在8°~12°范围内，且后压缩角小于前压缩角.
- 高超声速飞行器 /
- 三维内收缩 /
- 咽式进气道 /
- 流线追踪 /
- 计算流体动力学
Abstract: The design method of the three-dimensional inward turning hypersonic jaws inlet was introduced. Corresponding design codes were developed. Thereafter, a CFD technology was used to verify this method and the design codes with the generated jaws inlet model under the height of 30km, design Mach number of 5 and attack angle of 0°, respectively. Finally, geometry and aerodynamic performances of jaws inlet under design conditions affected by the design parameters, such as the streamline tracing outlet profile, the compression angle set of base field and the design Mach number, were compared and analyzed. Result shows that compared with a low aspect ratio, the geometry performance will be better if the aspect ratio of rectangle-outlet approaches 2 with shorter total length and smaller surface area. Moreover, the compression angles should be set between 8° and 12° in preliminary design for relatively better performances, with the latter compression angle smaller than the former.
- hypersonic vehicle /
- three-dimensional inward turning /
- jaws inlet /
- streamline tracing /
- CFD

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参考文献(22)

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