热科学学报（英文版）2001，Vol.10Issue(2)：97-102,6.
Preliminary Investigation of Full Model of Two-Mode Scramjet
Preliminary Investigation of Full Model of Two-Mode Scramjet
J.L. Le 1Z.C. Zhang 1H.C. Bai 1M.A. Goldfeld 2R.V. Nestoulia 2A.V. Starov3
作者信息
- 1. Centre of Aerodynamics Research and Development of China, Mianyang Sichuan, 62 1000, China
- 2. Institute of Theoretical and Applied Mechanics, Novosibirsk, Russia
- 3. Institute of Theoretical and Applied Mechanics, Novosibirsk, Russia
- 折叠
摘要
Abstract
In this paper results of previous researches of two-mode full engine model for Mach number range from3 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 ealculation results according to CFD and to approximate (engineering) methods. Tests were carried out without fuel supply (cold tests) and with fuel supply (studyof 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/experimentKey words
full engine/hypersonic flow/fuel/inlet/combustion/wind tunnel/experiment分类
能源科技引用本文复制引用
J.L. Le,Z.C. Zhang,H.C. Bai,M.A. Goldfeld,R.V. Nestoulia,A.V. Starov..Preliminary Investigation of Full Model of Two-Mode Scramjet [J].热科学学报（英文版）,2001,10(2):97-102,6.
