Shock-Boundary Layer Interaction in a Cornered Geometry

该项目隶属于流体动力学和空气动力学研究领域，涉及对角几何中超音速流动的激波边界层相互作用的研究。虽然激波对边界层的影响以及与之相关的分离已经被广泛地研究过，但控制角部等效的过程还没有得到很好的理解。该项目最初将涉及测量和描述存在于一个角落的边界层。当冲击引入该系统时，物理过程的复杂相互作用可以使用激光多普勒测速和粒子图像测速等方法进行研究。理解这种行为被认为是非常有趣的，无论是在增强我们对流体流动的描述方面，还是在超音速飞机上的应用方面，都使这成为空气动力学中一个令人兴奋的研究领域。

The project, falling under the Fluid Dynamics and Aerodynamics research area, involves the study of the shock-boundary layer interaction for supersonic flows in a cornered geometry.While the effect of a shock on the boundary layer, and the associated separation, has been extensively studied for a planar surface, the processes governing the equivalent at a corner are not well understood. The project would initially involve measuring and characterising the boundary layer which exists at a corner. The complex interplay of physical processes when a shock is introduced to this system can then be studied using methods such as laser Doppler velocimetry and particle image velocimetry. Understanding this behaviour is considered to be of significant interest, both in terms of enhancing our description of fluid flows and for applications in supersonic aircraft, making this an exciting field of study within aerodynamics.