TY - GEN
T1 - Numerical and experimental investigation on the RBCC engine nozzle in ejector mode
AU - Zhang, Zhengze
AU - Liu, Peijin
AU - Qin, Fei
AU - Wei, Xianggeng
AU - Lv, Xiang
AU - He, Guoqiang
PY - 2014
Y1 - 2014
N2 - The Rocket Based Combined Cycle (RBCC) engine, which integrates a high thrust to weight (T/W) rocket with a high specific impulse (Isp) airbreathing engine, shows its unique advantages as the potential propulsion candidate for the hypersonic vehicle. As the main component of thrust, the RBCC engine nozzle should be designed with a large expansion ratio when takes the wide flight envelope of the hypersonic vehicle into account. However, a serious over expansion occurs in the RBCC engine nozzle in ejector mode and results in the performance degradation. In this paper, numerical simulation and ground level static experiment are applied to investigate the operation characteristics of the RBCC engine nozzle in ejector mode. As a result, the flow separation appears in the subsonic status and the over expansion appears in the supersonic status inside the RBCC engine nozzle. Finally, an optimized nozzle configuration is designed, which improves its performance in ejector mode effectively.
AB - The Rocket Based Combined Cycle (RBCC) engine, which integrates a high thrust to weight (T/W) rocket with a high specific impulse (Isp) airbreathing engine, shows its unique advantages as the potential propulsion candidate for the hypersonic vehicle. As the main component of thrust, the RBCC engine nozzle should be designed with a large expansion ratio when takes the wide flight envelope of the hypersonic vehicle into account. However, a serious over expansion occurs in the RBCC engine nozzle in ejector mode and results in the performance degradation. In this paper, numerical simulation and ground level static experiment are applied to investigate the operation characteristics of the RBCC engine nozzle in ejector mode. As a result, the flow separation appears in the subsonic status and the over expansion appears in the supersonic status inside the RBCC engine nozzle. Finally, an optimized nozzle configuration is designed, which improves its performance in ejector mode effectively.
UR - http://www.scopus.com/inward/record.url?scp=84906993022&partnerID=8YFLogxK
M3 - 会议稿件
AN - SCOPUS:84906993022
SN - 9781624102844
T3 - AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
BT - AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2014
Y2 - 16 June 2014 through 20 June 2014
ER -