3D Hypersonic Shock-Turbulent-Boundary-Layer Interactions

激波与边界层的相互作用发生在高超声速飞行器上，并可导致高热和阻力增加。这是一个需要解决的重要设计问题。我们的目标是了解和量化的基本现象发生在这样的相互作用，使用国家的最先进的仪器和风洞设施。表面将被加热到真实的飞行温度，以准确地模拟飞行环境，并包括冷模型无法复制的效果。通过实验和数值模拟的结合，相互作用的3D特征的影响将导致对流动如何发展的新理解。未来高超音速飞行器的设计将受益于所获得的知识。

Shock-wave turbulent-boundary-layer interactions occur on hypersonic flight vehicles and can lead to high heating and increased drag. This is a paramount design issue that needs addressing. We aim to understand and quantify fundamental phenomena occurring in such interactions using state-of-the-art instrumentation and wind-tunnel facilities. Surfaces will be heated to realistic flight temperatures to simulate accurately the flight environment and include effects not reproduced with cold models. The effects of 3D features of the interactions will lead to new understanding of how the flow develops through a combination of experiments and numerical simulations. Future designs of hypersonic flight vehicles will benefit from knowledge gained.