Transitional wave configurations between Type Ⅲ and Type Ⅳ oblique-shock/bow-shock interactions  

作　　者：Jun PENG Shuai LI Fan YANG Mingyue LIN Guilai HAN Zongmin HU 

机构地区：[1]State Key Laboratory of High-temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China [2]The System Design Institute of Mechanical-Electrical Engineering,Beijing 100854,China [3]School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China

出　　处：《Chinese Journal of Aeronautics》2023年第3期96-106,共11页中国航空学报（英文版）

基　　金：co-supported by the National Key Research and Development Plan of China(No.2019YFA0405204);the National Natural Science Foundation of China(Nos.12172365,12072353 and 12132017)。

摘　　要：The interactions of oblique/bow shock waves are the key flow phenomena restricting the design and aerothermodynamic performance of high-speed vehicles.Type Ⅲ and Type Ⅳ Shock/Shock Interactions(SSIs)have been extensively investigated,as such interactions can induce abnormal aerodynamic heating problems in hypersonic flows of vehicles.The transition process between these two distinct types of shock/shock interactions remains unclear.In the present study,a subclass of shock/shock interaction configuration is revealed and defined as Type Ⅲa.Type Ⅲa interaction can induce much more severe aerodynamic heating than a Type Ⅳ interaction which was ever reported to be the most serious in literature.The intense aerodynamic heating observed in this configuration highlights a new design point for the thermal protection system of hypersonic vehicles.A secondary Mach interaction between shock waves in the supersonic flow path of a Type Ⅲ configuration is demonstrated to be the primary mechanism for such a subclass of shock/shock interaction configuration.

关 键 词：Shock interactions Transitional configuration Aerodynamic heating Shear layer Mach interaction 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V411