Affiliation of Author(s):能源与动力学院
Journal:Tuijin Jishu
Abstract:With increasing urgent demand of long-range and wide-range Mach number high speed vehicle, Scramjet, even Turbine Based Combined Cycle(TBCC), etc., have become the research focus all over the world. Propulsion system is the key of hypersonic vehicle to achieve high efficiency in wide operation corridor, and Single Expansion Ramp Nozzle (SERN) is one of the most important parts and key technologies of propulsion system. The special requirements of the exhaust nozzle for long-range and wide-range Mach number high speed vehicle are analyzed, the relative progress all around the world is reviewed briefly, the main work and research progress of the design method for scramjet nozzle and TBCC exhaust system by our group are mainly introduced. The results show that the SERN profiles designed by different method have great effects on the aerodynamic performances of nozzle under high Nozzle Pressure Ratio (NPR). Finally, the future research project is proposed. This paper is aimed at concluding the recent research progress, analyzing the key problem of science and technology, and providing the reference and suggestions for the future research. © 2018, Editorial Department of Journal of Propulsion Technology. All right reserved.
ISSN No.:1001-4055
Translation or Not:no
Date of Publication:2018-10-01
Correspondence Author:Xu Jinglei