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无隔道进气道反设计及附面层排除机理分析
引用本文:梁德旺,李博.无隔道进气道反设计及附面层排除机理分析[J].航空学报,2005,26(3):286-289.
作者姓名:梁德旺  李博
作者单位:南京航空航天大学,能源与动力学院,江苏,南京,210016
基金项目:“十五”空军预研资助项目
摘    要: 采用"照片三维复原技术"对某型飞机无隔道进气道/前机身进行了几何重构,然后用N-S方程对机身/进气道内外流场进行了数值模拟,得到了进气道内外流场的马赫数分布和鼓包表面的压力分布,分析了无隔道进气道排移附面层的机理。结果表明:该飞机进气道在鼓包顶点有一个起始压缩角,波后为等熵压缩面。研究认为,无隔道进气道的设计机理是在鼓包压缩面上形成一个中间高、两侧低的压力分布,在该压力梯度的作用下来流附面层被推向两侧并被排除。

关 键 词:无隔道进气道  鼓包进气道  一体化设计  计算流体力学  
文章编号:1000-6893(2005)03-0286-04
修稿时间:2004年3月19日

Reverse Design of Diverterless Inlet and Mechanism of Diversion of Boundary Layer
LIANG De-wang,LI Bo.Reverse Design of Diverterless Inlet and Mechanism of Diversion of Boundary Layer[J].Acta Aeronautica et Astronautica Sinica,2005,26(3):286-289.
Authors:LIANG De-wang  LI Bo
Institution:College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Abstract:The diverterless inlet and forebody of a fighter are constructed by using the Three Dimensional Reversion Technique of Photos and the external and internal flowfields of the inlet and forebody are calculated.The Mach contours inside and outside the inlet and the pressure distribution on the bump surface are presented.Mechanism of diversion of boundary layer on diverterless supersonic inlet (DSI) is also analyzed.It can be seen from the results that there is an initial compression angle at the front point of the bump and an isoentropic compression surface after the shock.The investigation shows that the diverterless supersonic inlet or bump inlet creates a high pressure area on the bump compression surface which pushes the air in boundary layer away from the inlet.
Keywords:divertreless supersonic inlet (DSI)  bump inlet  integrated design  computational fluid dynamics (CFD)
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