Effect of Free-Stream Mach Number on the Base Thermal Environment of LaunchVehicle  

作　　者：WANG Xu XU Xu YU Jiaqi YANG Qingchun 

机构地区：[1]School of Astronautics,Beihang University,Beijing 100191,China [2]Shenyuan Honors College,Beihang University,Beijing 100191,China

出　　处：《Journal of Thermal Science》2024年第6期2426-2436,共11页热科学学报（英文版）

基　　金：supported by the Outstanding Research Project of Shen Yuan Honors College;Academic Excellence Foundation of BUAA for PhD Students;National Key Laboratory of aerospace liquid propulsion

摘　　要：Convective heating of the rocket base caused by high-temperature reverse flow has long been a focus of thermal protection research.With distinctive structural characteristics,the base thermal environment of a twin-nozzle engine proves more susceptible to the recirculation region than its multi-nozzle counterparts.During the transonic stage,significant alterations in the flow field structure at the rocket base strongly influence the recirculation region.This study investigated the thermal environment of the rocket base with a twin-nozzle configuration in freestream at Mach numbers of 0.6 to 3.0.Results indicate that the freestream Mach number significantly affects the thermal environment at the rocket base during the transonic stage.The increase of Mach number from 0.6 to 1.0 causes the convective heating of the rocket base to increase by 7.7 times.This phenomenon arises due to the plume-induced shock wave caused by the impact of the supersonic free shear layer and plume shear layer while the flight speed exceeds the sound speed.The interaction between the shock wave and the shear layer amplifies turbulence in the recirculation region and at the inflection point,resulting in a stronger high-temperature reverse flow.In addition,the cause of low-altitude base heating was analyzed,and it was found that the mechanism is different from the high-temperature countercurrent effect caused by plume interaction.

关 键 词：rocket base heating free stream Mach number shock-turbulence interaction twin-nozzle 

分 类 号：V475.1[航空宇航科学与技术—飞行器设计]