一种基于双模态燃烧二元高超声速进气道研究

李航; 李博

一种基于双模态燃烧二元高超声速进气道研究

李航^1,2, ,,
李博¹

1.
南京航空航天大学能源与动力学院,南京 210016
2.
中国人民解放军 92724部队,山东青岛 266000

基金项目: 南京航空航天大学基本科研业务费专项科研项目(NS2010040)

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出版历程
- 收稿日期: 2011-08-19
- 刊出日期: 2012-07-28

Research on two-dimensional hypersonic inlet based on dual-mode combustion

LI Hang^{1,2
, ,},
LI Bo¹

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
2.
Unit 92724,the Chinese People's Liberation Army,Qingdao Shandong 266000,China

摘要

摘要: 设计并研究了一种基于双模态燃烧的二元高超声速进气道.通过在进气道内设计一个隔板,将流道分为超声速通道和亚燃通道.采用数值模拟方法,研究了内压段肩部型面,隔板进口高度及水平位置,过渡段起始点及扩张角、下通道出口高度、隔板头部型面等几何设计参数对进气道性能的影响规律,并给出了参数选择建议.结果表明:在研究范围内,内压段肩部型面、隔板进口高度及水平位置和过渡段起始点对总压恢复系数影响较大;而隔板进口高度及头部型面、过渡段扩张角和下通道出口高度对抗反压能力有较大影响.
- 高超声速进气道 /
- 双模态超燃冲压发动机 /
- 数值模拟 /
- 隔板 /
- 反压特性
Abstract: Design and study of a two-dimensional hypersonic inlet based on dual-mode combustion was conducted.The duct was divided into a supersonic duct and a subsonic combustion duct by a splitter plate.The influence of the geometry parameters on the inlet performance was mainly studied by using numerical method.The geometry parameters included the profile of the shoulder,the height and position of splitter plate,the turning position and expansion angle of transition duct,the height of subsonic combustion duct and the shape of the head of splitter plate.Results indicate that the profile of the shoulder,the height and position of splitter plate,the turning position of transition duct have great effects on the total pressure recovery coefficient,while the height of splitter plate,the shape of the head of splitter plate,the expansion angle of transition duct and the height of subsonic combustion duct have great effects on characteristics of back pressure.
- hypersonic inlet /
- dual-mode scramjet /
- numerical simulation /
- splitter plate /
- characteristics of back pressure

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参考文献(14)

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