进口型线水平投影可控的变截面内收缩进气道设计

doi:10.7527/S1000-6893.2016.0270

流体力学与飞行力学

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进口型线水平投影可控的变截面内收缩进气道设计

李永洲¹, 孙迪², 张堃元³, 郭世亮¹

1. 中国航天科技集团公司航天系统发展研究中心, 北京 100094;
2. 中国航天科技集团公司西安航天动力技术研究所, 西安 710025;
3. 南京航空航天大学能源与动力学院, 南京 210016

收稿日期:2016-07-25 修回日期:2016-09-21 出版日期:2017-05-15 发布日期:2016-10-10
通讯作者: 李永洲 E-mail:nuaa-2004@126.com
基金资助:
国家自然科学基金（90916029）

Design on variable section inward turning inlet with controlled horizontal projection of intake curve

LI Yongzhou¹, SUN Di², ZHANG Kunyuan³, GUO Shiliang¹

1. Aerospace System Development Research Center, China Aerospace Science and Technology Corporation, Beijing 100094, China;
2. Xi'an Institute of Aerospace Propulsion Technology, China Aerospace Science and Technology Corporation, Xi'an 710025, China;
3. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2016-07-25 Revised:2016-09-21 Online:2017-05-15 Published:2016-10-10
Supported by:
National Natural Science Foundation of China (90916029)

摘要/Abstract

摘要：

发展了一种进口型线水平投影可控的三维变截面内收缩进气道设计方法。基于反正切马赫数分布基准流场，在指定进口型线水平投影为椭圆和出口为圆的条件下，结合流线追踪和截面渐变技术设计了光滑过渡的内收缩进气道。在设计点（Ma_i=5.4）和接力点（Ma_i=4.0）对其进行数值仿真，计算结果表明，设计点时进气道的主要流动特性与基准流场基本一致，无黏时可以捕获98%的自由来流，喉道性能与基准流场基本相等。相对椭圆进口进气道，截面渐变的椭圆转圆进气道流场结构相似且性能下降较小，有黏条件下设计点和接力点时喉道总压恢复系数分别降低了2.9%和1.2%。此外，该进气道表现出良好的总体性能，接力点的流量系数达0.82。

关键词: 高超声速, 内收缩进气道, 水平投影, 截面渐变, 流线追踪

Abstract:

A design method is developed for three-dimensional variable section inward turning inlet with controlled horizontal projection of intake curve. Based on the basic flowfield with arc tangent Mach number distribution, the inward turning inlet with smooth shape transition from an elliptical horizontal projection of intake curve to a circular exit is designed utilizing streamline tracing and shape transition techniques. Numerical simulation is conducted at the design point (Ma_i=5.4) and the relay point (Ma_i=4.0). The results indicate that the inlet is of the major features of the basic flowfield, and 98% free incoming flow at the design point can be captured under the inviscid condition. The performance of the throat plane is close to the basic flowfield. In comparison with the inlet of elliptical intake, the variable section inlet with elliptical-to-circular transition has similar flowfield structure and slightly lower performance. Under the viscous condition, the total pressure recovery coefficient of the throat plane reduces 2.9% and 1.2% at the design point and the relay point, respectively. In addition, the inlet has high overall performance, and the flow coefficient reaches 0.82 at the relay point.

Key words: hypersonic, inward turning inlet, horizontal projection, shape transition, streamline tracing

中图分类号:

V231.3

李永洲, 孙迪, 张堃元, 郭世亮. 进口型线水平投影可控的变截面内收缩进气道设计[J]. 航空学报, 2017, 38(5): 120640-120640.

LI Yongzhou, SUN Di, ZHANG Kunyuan, GUO Shiliang. Design on variable section inward turning inlet with controlled horizontal projection of intake curve[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(5): 120640-120640.

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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

进口型线水平投影可控的变截面内收缩进气道设计

Design on variable section inward turning inlet with controlled horizontal projection of intake curve

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