Investigation of flow characteristic and performance on the "Jaws" hypersonic inlet

DONG Hao; WANG Cheng-peng; CHENG Ke-ming

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Investigation of flow characteristic and performance on the "Jaws" hypersonic inlet

更新时间：2026-07-07

- Investigation of flow characteristic and performance on the "Jaws" hypersonic inlet
- Vol. 24, Issue 11, (2009)
- 作者机构：
  
  南京航空航天大学航空宇航学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
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DONG Hao, WANG Cheng-peng, CHENG Ke-ming. Investigation of flow characteristic and performance on the "Jaws" hypersonic inlet[J]. 2009, 24(11).
DOI：

DONG Hao, WANG Cheng-peng, CHENG Ke-ming. Investigation of flow characteristic and performance on the "Jaws" hypersonic inlet[J]. 2009, 24(11). DOI：

摘要

采用数值模拟的方法比较分析了一种矩形型面的内收缩进气道和一种椭圆型面的"咽"式进气道的流动特性和性能.这两种内收缩进气道都是以四道平面斜激波三维流场为基本流场

利用流线追踪技术得到的.研究结果表明

该"咽"式进气道对设计状态下的攻角变化不太敏感;在非设计状态下具有较高的流量捕获和压缩能力;另外

由于其浸湿面积小

进气道内附面层增长缓慢

激波与附面层干扰较弱.因此

这种"咽"式流道可作为吸气式高超声速飞行器进气道的一个有利选择方案.

Abstract

Two different inward turning inlets

i.e.a classic rectangular cross-section and a "Jaws" one

were explored numerically.Based on a three dimensional flowfield with four planar shock waves

these two were derived with the technology of streamtracing.Results indicate: the performance of the "Jaws" inward inlet is insensitive to the angles of attack on design point;the inlet has high mass capture and compression capability on off-design point;in addition

boundary-layer growth of the inlet develops slowly and shock/boundary-layer interaction is weak because of the diminished wetted area.In conclusion

this "Jaws" inward inlet is an advantageous option of the hypersonic inlet.

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Related Institution

中国航天科技集团有限公司西安航天动力研究所

中国航天科技集团有限公司航天系统发展研究中心

南京航空航天大学能源与动力学院

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

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