Influence of the shock wave‑turbulence interaction on the swirl distortion in hypersonic inlet  

作　　者：Zhenlong Wu Yiqing Li Limei Lu Xinyi Xu Ranhui Liang 

机构地区：[1]School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China [2]Shanghai Space Propulsion Technology Research Institute,Shanghai 201112,China

出　　处：《Advances in Aerodynamics》2024年第1期123-143,共21页空气动力学进展(英文)

基　　金：This research was funded by the National Natural Science Foundation of China(Grant No.12002144);the Jiangxi Provincial Natural Science Foundation(Grant No.20212BAB211015).

摘　　要：This study uses the Large Eddy Simulation(LES)technique to conduct an exhaustive analysis of the flow characteristics within the Rectangular-to-Elliptical shape Transition(REST)inlet under Mach 6 conditions.It mainly focuses on investigating the influ-ence of the shock wave-turbulence interaction on the swirl distortion at the inlet exit.At the design condition,characterized by 0°Attack and 0°Sideslip,the inci-dent shock wave at the inlet lip undergoes multiple reflections within the bound-ary layer of the domain wall,culminating in the formation of turbulent structures.The first reflected shock wave has the highest energy,exerting a significant impact on the boundary layer and the exit swirl distortion.On the contrary,the energy of the incident shock wave is progressively reduced due to repeated reflections,which results in reducing the exit swirl distortion.Under off-design conditions,characterized by 6°Attack and 0°Sideslip as well as 6°Attack with 6°Sideslip,varia-tions in the incoming flow make the incident shock wave move inward,decreasing the frequency of shock wave reflections and even significantly reducing the reflected shock waves under conditions of 6°Attack and 6°Sideslip.However,this results in significantly increasing the exit swirl angle and distortion intensity.The obtained results demonstrate that changes in the incoming flow conditions significantly affect the level of exit swirl distortion by modulating the shock wave-turbulence interaction,especially in terms of the positioning of the incident shock wave and the quantity of reflected shock waves.In addition,this paper studies the wall heat transfer coeffi-cient of the inlet.The obtained results show that the interaction between shock waves and the boundary layer significantly affects the heat transfer coefficient.This study pro-vides a foundation for the comprehension and prediction of the performance of hyper-sonic inlets across a spectrum of flight conditions,and for the guidance of the design and optimization of such inlets.

关 键 词：REST inlet Hypersonic inlet Large eddy simulation TURBULENCE Swirl distortion measurement 

分 类 号：O35[理学—流体力学]