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

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

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.

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 meth- od applied the rotational method of characteristics to design the basic axisymmetric flowfield and applied stream tracing techniques to generate an inviscid configuration, and then, de signed final inlets with viscous correction. Several categories of typical basic flowfield de- signed under the same constraint were analyzed comparatively. The hypersonic inward turn ing 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 in lets 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.