进气道内激波 /边界层干扰及控制研究进展

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

关键词:  进气道  激波  边界层干扰  流动控制

Key words:  Inlet  Shock wave  Boundary layer interaction  Flow control

摘要:

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。

Abstract:

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. 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 make its prediction go beyond the scope of current shock/boundary layer interaction theory. A brief summary on related research of shock/boundary layer interaction and its control methods in high speed inlets was given.