CARET进气道亚音速气动特性研究

朱宇; 李椿萱; 李天

CARET进气道亚音速气动特性研究

1.
北京航空航天大学飞行器设计与应用力学系
2. 沈阳飞机设计研究所

详细信息

中图分类号: V 2313
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- 被引次数: 0
出版历程
- 收稿日期: 2002-04-01
- 网络出版日期: 2003-06-30

Studies of a Caret Inlet at Subsonic Speeds

1.
Dept. of Flight Vehicle Design and Applied Mechanics, Beijing University of Aeronautics and Astronautics
2. Shenyang Aircraft Design Research Institute

摘要

摘要: 通过对一种Caret型进气道进行试验与流场数值计算研究,给出该型进气道亚音速的基本气动特性.在低速情况下,进/发匹配点处由于流量系数较大,管道内往往存在分离,这是总压恢复降低的主要原因.试验表明在进气道出口的左上角存在低能量区,而数值计算显示在进口外下角处首先出现流动分离,分离在管道内发展时并未沿周向旋转.
- 进气道 /
- 数值模拟 /
- 流动分离 /
- Caret
Abstract: A Caret inlet was studied by means of experiment and numerical simulation. Basic aerodynamic characteristics of the inlet at low and subsonic speeds were presented. The experimental as well as computational results revealed that flow separations may exist at match state of inlet/engine at low speeds due to the existence of large mass flow rate coefficients. It was the true mechanism causing the low total pressure recovery in the inlet as demonstrated. Experimental results show a low total pressure region being taken place at the upper left corner of the duct exit, which is matched with the results obtained by numerical computations showing that flow separations on set occurs at the low-outboard corner of inlet entrance and develop with no circumrotation.
- air inlets /
- numerical simulation /
- flow separation /
- Caret

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参考文献(1)

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