Shock-Boundary Layer Interaction in a Cornered Geometry

该项目属于流体动力学和空气动力学研究领域，涉及角几何形状中超音速流的激波-边界层相互作用的研究。虽然平面表面上激波对边界层的影响以及相关的分离已得到广泛研究，但角处控制等效物的过程还没有得到很好的理解。该项目最初将涉及测量和表征存在于拐角处的边界层。当冲击被引入到这个系统中时，物理过程的复杂相互作用可以使用诸如激光多普勒测速和粒子图像测速的方法来研究。了解这种行为被认为是显着的利益，无论是在加强我们的流体流动的描述和应用程序在超音速飞机，使这一令人兴奋的研究领域内的空气动力学。

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.