Investigation of thermal protection system by forward-facing cavity and opposing jet combinatorial configuration  

作　　者：Lu Haibo Liu Weiqiang 

机构地区：[1]Science and Technology on Scramjet Laboratory, National University of Defense Technology [2]Nanjing Artillery Academy

出　　处：《Chinese Journal of Aeronautics》2013年第2期287-293,共7页中国航空学报（英文版）

基　　金：co-supported by National Natural Science Foundation of China (No. 90916018);Research Fund for the Doctoral Program of Higher Education of China (No.200899980006)

摘　　要：This paper focuses on the usage of the forward-facing cavity and opposing jet combinatorial configuration as the thermal protection system （TPS） for hypersonic vehicles. A hemispherecone nose-tip with the combinatorial configuration is investigated numerically in hypersonic free stream. Some numerical results are validated by experiments. The flow field parameters, aerodynamic force and surface heat flux distribution are obtained. The influence of the opposing jet stagnation pressure on cooling efficiency of the combinatorial TPS is discussed. The detailed numerical results show that the aerodynamic heating is reduced remarkably by the combinatorial system. The recirculation region plays a pivotal role for the reduction of heat flux. The larger the stagnation pressure of opposing jet is, the more the heating reduction is. This kind of combinatorial system is suitable to be the TPS for the high-speed vehicles which need long-range and long time flight.This paper focuses on the usage of the forward-facing cavity and opposing jet combinatorial configuration as the thermal protection system （TPS） for hypersonic vehicles. A hemispherecone nose-tip with the combinatorial configuration is investigated numerically in hypersonic free stream. Some numerical results are validated by experiments. The flow field parameters, aerodynamic force and surface heat flux distribution are obtained. The influence of the opposing jet stagnation pressure on cooling efficiency of the combinatorial TPS is discussed. The detailed numerical results show that the aerodynamic heating is reduced remarkably by the combinatorial system. The recirculation region plays a pivotal role for the reduction of heat flux. The larger the stagnation pressure of opposing jet is, the more the heating reduction is. This kind of combinatorial system is suitable to be the TPS for the high-speed vehicles which need long-range and long time flight.

关 键 词：Aerodynamic heating Forward-facing cavity Hypersonic flow Opposing jet Thermal protection system 

分 类 号：V215.4[航空宇航科学与技术—航空宇航推进理论与工程]