Supersonic/ Hypersonic Flow Research for the High Speed Propulsion

摘要：

This article describes two example research works on the supersonic inlet flow, and supersonic combustion flow in the model Scramjet engine for the hypersonic propulsion. First, an experimental and numerical study of supersonic inlet is presented. This study was conducted on a two type of inlet models, rectangular and axisymmetric; two models were designed by same method with similar size (about 160mm) and tests were done at Mach 2.5. For second case, supersonic combustion experiments were performed using three different types of fuel injectors in the cavity based combustor with various combustor inlet and fuel flow conditions.

关键词： Supersonic Hypersonic Scramjet

作者: In-Seuck Jeung

作者单位: Department of Aerospace Engineering, Seoul National University, Seoul, 151-744, Korea

会议类型: 国际会议

会议名称: 2008 National Academic Symposium for Ph. D. Candidates and Tri-University Workshop on Aero-Structural Mechanics & Aerospace Engineering(NASPCTUWMAE2008)(2008年国际航天航空工程会议暨2008年博士生学术会议(力学))

会议地点: 北京

会议语种:英文

页码: 1-4

在线出版日期: 2008-10-23（万方平台首次上网日期，不代表论文的发表时间）