Effect of suction on performance of inward turning inlet with rectangular-to-circular shape transition

被引：0

作者：

Li Y. ^{[1
,2
]}

Zhang K. ^{[1
]}

Sun D. ^{[3
]}

机构：

[1] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing

[2] Xi'an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi'an

[3] Xi'an Institute of Aerospace Propulsion Technology, China Aerospace Science and Technology Corporation, Xi'an

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2016年 / 37卷 / 12期

基金：

中国国家自然科学基金;

关键词：

Inward turning inlet; Starting performance; Suction; Vortex region; Wind tunnel test;

D O I：

10.7527/S1000-6893.2016.0065

中图分类号：

学科分类号：

摘要：

Various suction schemes are designed for an inward turning inlet with rectangular-to-circular shape transition with controlled Mach number distribution. Experiments and numerical simulations are conducted to analyze the influence of the scheme on the performance of the inlet. The operation characteristics of the design point and the self-starting performance are obtained. The experimental results validate that suction can efficiently improve the performance of the inlet. The bleeding in the downwash concentration region of the top wall can obviously reduce the exit vortex region and improve the back pressure resistance. Compared with those of the original inlet, the total pressure recovery coefficient increases by 3.8% and the critical back pressure increases from 135 times of the free stream static pressure to 150 times at the exit section on the design point (Ma=6.0), when the relative bleeding flux is 0.99%. In addition, the bleeding in the separation region of the top wall can promote the starting ability. When Ma=5.0 and AOA=4°, the inlet realizes self-starting with the relative bleeding flux being 0.78%. When the inlet restarts, the corresponding compression ratio and the total pressure recovery coefficient at the exit section are 30.6 and 0.600, respectively. © 2016, Press of Chinese Journal of Aeronautics. All right reserved.

引用

页码：3625 / 3633

页数：8

共 23 条

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