The vast majority of shock wave–boundary-layer interactions in practical applications like supersonic aircraft intakes are three dimensional in nature. The complex behaviour of such interactions can generally be understood by combining the flow physics of a limited number of canonical cases. The physical understanding of these flow fields developed by numerous investigators over the last half century is reviewed, focusing predominantly on steady aspects of turbulent, uncontrolled interactions in the transonic and supersonic regimes, i.e. for Mach number less than 5. Key physical features of the flow fields and recent developments are described for swept compression corners, various fin interactions, semi-cones, vertical cylinder-induced interactions, swept oblique shock reflections and flared cylinders. In addition to the canonical geometries, a different type of three dimensionality concerning sidewall effects in duct flows, like intakes or propulsion systems, is also reviewed. The underlying mechanisms, centred on pressure waves propagating from the corner regions, are introduced and the implications for separation unsteadiness and flow control are discussed.

在超音速飞机进气等实际应用中，绝大多数冲击波-边界层相互作用本质上是三维的。这种相互作用的复杂行为通常可以通过结合有限数量的典型案例的流动物理学来理解。回顾了过去半个世纪许多研究人员对这些流场的物理理解，主要关注跨音速和超音速范围内湍流、不受控制的相互作用的稳定方面，即马赫数小于 5。流动的关键物理特征描述了扫掠压缩角、各种翅片相互作用、半锥体、垂直圆柱体引起的相互作用、掠过倾斜冲击反射和扩口圆柱体的领域和最新进展。除了规范的几何形状之外，还回顾了与管道流中的侧壁效应有关的不同类型的三维度，例如进气口或推进系统。介绍了以从角部区域传播的压力波为中心的基本机制，并讨论了分离不稳定和流动控制的影响。