Preliminary Investigation of Full Model of Two-Mode Scramjet  

作　　者：J.L.Le M.A.Goldfeld 等 

机构地区：[1]CentreofAerodynamicsResearchandDevelopmentofChina,MianyangSichuan621000,China [2]InstituteofTheoreticala

出　　处：《Journal of Thermal Science》2001年第2期97-102,共6页热科学学报（英文版）

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.

关 键 词：full engine hypersonic flow FUEL INLET COMBUSTION wind tunnel experiment. 

分 类 号：V47[航空宇航科学与技术—飞行器设计] TK413.84[动力工程及工程热物理—动力机械及工程]