Mach reflection and pressure/heating loads on V-shaped blunt leading edges with variable cross-sections and crotches  

作　　者：Tao ZHANG Xuhui ZHANG Luoyu RAO Chongguang SHI Chengxiang ZHU Yancheng YOU 

机构地区：[1]School of Aerospace Engineering,Xiamen University,Xiamen 361005,China [2]China Academy of Aerospace Science and Innovation,Beijing 100176,China

出　　处：《Chinese Journal of Aeronautics》2025年第1期271-285,共15页中国航空学报(英文版)

基　　金：support of the National Natural Science Foundation of China(Nos.U20A2069,12302389,12372295);the Natural Science Foundation of Fujian Province,China(No.2023J01046)。

摘　　要：The primary Mach Reflection(MR)and pressure/heating loads on V-shaped Blunt Leading Edges(VBLEs)with variable elliptic cross-sections and conic crotches are theoretically investigated in this study.The simplified continuity method is used to forecast the shock configurations.The theoretical predictions and the numerical simulations for the Mach stem and the triple point as well as the curved shock accord well.Based on the theoretical model,an analysis of the impact of the axial ratio a/b of the cross-sectional shape and the eccentricity e of the crotch sweep path on shock structures is carried out.The shock configurations obtained from the theoretical model enable the derivation of the transition boundaries between the primary MR and the same family Regular Reflection(sRR).It is found that the increase of a/b and e can both facilitate the primary MR to sRR transition.The resulting transition and the corresponding generation of the wall pressure and heat flux are then investigated.The results indicate that higher values of the ratio a/b can significantly reduce the wall pressure and heating loads by inducing the primary MR to sRR transition.Conversely,the increase in the eccentricity e results in increased loads,despite causing the same transition.

关 键 词：AERODYNAMICS Hypersonic flow Shock waves Heat flux V-shaped blunt leading edges 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]