Preliminary Investigation of Full Model of Two-Mode Scramjet

作     者：J.L.Le M.A.Goldfeld 等 

作者机构：CentreofAerodynamicsResearchandDevelopmentofChinaMianyangSichuan621000China InstituteofTheoreticala 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2001年第10卷第2期

页      面：97-102页

核心收录：

学科分类：080703[工学-动力机械及工程] 08[工学] 0807[工学-动力工程及工程热物理] 0805[工学-材料科学与工程（可授工学、理学学位）] 082503[工学-航空宇航制造工程] 0825[工学-航空宇航科学与技术] 0702[理学-物理学] 

主　　题：full engine hypersonic flow fuel inlet combustion wind tunnel experiment. 

摘      要：In this paper results of previous researches of two-mode full engine model for Mach number range from 3 to 6 are presented. The main aims of researches are to obtain characteristics of full engine model and its components (the inlet, the combustion chamber and the nozzle) in ramjet and scramjet regimes and to compare these characteristics with the calculation results according to CFD and to approximate (engineering) methods. Tests were carried out without ha supply (cold tests) and with fuel supply (study of ignition and combustion).Hydrocarbon and hydrogen fuel (gaseous or liquid) were used during the tests.