基于马赫数分布规律可控概念的高超声速内收缩进气道设计

李永洲; 张堃元; 南向军

基于马赫数分布规律可控概念的高超声速内收缩进气道设计

南京航空航天大学能源与动力学院, 南京 210016

基金项目: 国家自然科学基金(90916029)

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出版历程
- 收稿日期: 2011-11-21
- 刊出日期: 2012-11-28

Design of hypersonic inward turning inlets base on concept of controllable Mach number distribution

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 提出了一种高超声速内收缩进气道设计方法.在壁面马赫数分布规律给定的前提下,通过有旋特征线法反设计出轴对称基准流场,采用流线追踪技术来生成进气道的无黏型面并通过黏性修正得到进气道最终构型.对相同约束条件下设计的几种典型马赫数分布规律的基准流场进行对比分析,选取了反正切马赫数分布规律设计基准流场进而生成一种圆形进口的高超内收缩进气道,数值仿真结果显示:这种进气道具有良好的流量捕获特性和较高的压缩效率,表明提出的设计方法可行,拓宽了基准流场的选择范围,值得进一步深入研究.
- 高超声速进气道 /
- 内收缩进气道 /
- 马赫数分布规律 /
- 设计方法 /
- 数值仿真
Abstract: A method has been devised for the design of hypersonic inward turning inlets.On condition that the Mach number distribution along the surface has been given,this method applied the rotational method of characteristics to design the basic axisymmetric flowfield and applied stream tracing techniques to generate an inviscid configuration,and then,designed final inlets with viscous correction.Several categories of typical basic flowfield designed under the same constraint were analyzed comparatively.The hypersonic inward turning inlets with circular shape intake were designed using the basic flowfield of arc tangent Mach number distribution.The numerical simulation results indicate that the category of inlets has good mass capture ratio and compression efficiency.This design method is feasible and extends the scope of basic flowfield,so it deserves further investigations.
- hypersonic inlet /
- inward turning inlet /
- Mach number distribution /
- design method /
- numerical simulation

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参考文献(20)

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