Symmetric Mach reflection configuration with asymmetric unsteady solution  

作　　者：Chenyuan BAI Miaomiao WANG Ziniu WU 

机构地区：[1]Ministry of Education Key Laboratory of Fluid Mechanics,Beihang University,Beijing 100083,China [2]Department of Engineering Mechanics,Tsinghua University,Beijing 100084,China

出　　处：《Chinese Journal of Aeronautics》2023年第4期75-78,共4页中国航空学报（英文版）

基　　金：supported partly by the National Key Project,China(No.GJXM92579);the National Science and Technology Major Project,China(No.2017-II-003-0015);the National Natural Science Foundation of China(Nos.11721202,52192632);the Young Elite Scientists Sponsorship Program of CAST,Young Talent Support Plan of Beihang University.

摘　　要：Symmetric Mach reflection in steady supersonic flow has been usually studied by solving a half-plane problem with the symmetric line treated as reflecting surface,thus losing the opportunity to discover antisymmetric flow structures.Here in this paper we treat this problem as an entire-plane problem.Using an unsteady numerical approach,we find that the two sliplines exhibit antisymmetric unsteadiness if the Mach stem height is small while the flow remains symmetric if the Mach stem height is large.The mechanism by which disturbance,generated in the downstream of the flow duct between the two sliplines,propagates upstream is identified and it is also shown that the interaction between the transmitted expansion waves and the sliplines increases the amplitude of the unstable modes.The present study suggests a new type of compressible jet that deserves further studies.

关 键 词：Antisymmetric solution Mach reflection Shock reflection Supersonic flow 

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