进气道内激波/边界层干扰及控制研究进展

进气道作为高速航空航天飞行器的重要气动部件,对飞行器的气动力特性、结构重量、隐身性能等有显著影响。激波/边界层干扰现象是高速进气道内普遍存在的一类流动现象,对进气道的性能有突出的影响。发生于进气道内的激波/边界层干扰现象主要可分为正激波/边界层干扰、斜激波/边界层干扰以及三维激波/边界层干扰几类,由于受到侧壁壁面和进气道内背景波系的影响,这些干扰现象偏离了传统基于简化模型的研究结果,具有显著的耦合干扰特征,干扰区间内三维特征明显。概述了发生于进气道内的激波/边界层干扰特性及相关研究进展,并对目前进气道内激波/边界层干扰现象的控制方法进行了总结。

Progress of Shock Wave/Boundary Layer Interactionand Its Control in Inlet

Inlet is an important aerodynamic component of a high speed aeronautical and aerospace vehicle. The aerodynamic performance, weight and stealth performance of the vehicle is largely dictated by the inlet. Shock/boundary layer interaction is a common phenomenon in a high speed inlet and plays an important role in the inlet performance. This paper gives a brief summary on related research of shock/boundary layer interaction and its control in inlets. The shock/boundary layer interaction in inlets can be classified into normal shock/boundary layer interaction, oblique shock/boundary layer interaction and three-dimensional shock/boundary layer interaction. Due to the effects of sidewall and complex background waves, the shock/boundary layer interaction in the inlet embodies significant three-dimensional character and remarkable coupling effect which makes its prediction go beyond the scope of current shock/boundary layer interaction theory. Till now many control methods such as bleeding, microvortex generator, surface bump and et al. have been developed to control the shock/boundary layer interaction. However, there are a lot of basic issues to solve the shock/boundary layer interaction occurred in inlets which embodies the prominent features of supersonic, multiple shock interaction and variable cross-section.