Numerical and Ezperimental Investigation of Supersonic Intake at a Wide Mach-number Range
Supersonic intakes of ramjets compress the incoming high velocity airflow and transfer the kinetic energy of the airflow into potential energy efficiently. The value and range of an intake operating Mach-number has important effect on its performance. The higher Mach-number and the wider Mach range,the more difficult to get high intake performance. In this paper,the results of numerical simulation and wind-tunnel tests of a supersonic intake working from Ma 2. 5 to Ma 4. 0 are reported. The result of velocity characteristics, throttling characteristics, attack angle characteristics, cowl pressure distribution along the axial direction, start characteristics, subcritical characteristics, and the outlet flow field are introduced. The specific lag in the throttling loop of the mixed compression intake is observed at Ma 2. 5 and the intake can start at this Mach number. Good performance, such as critical total pressure recovery, stability margin at subcritical operating conditions, has been achieved at Ma 4.0. The performance obtained from numerical simulation agrees with the experimental result.
Ramjet Supersonic Intake Wind Tunnel Test Intake Operating Characteristics
Yang Baoe Guo Bin Yang Tiecheng Wu Baoyuan Luan Xiting Wang Liang
Northwestern Polytechnical University,School of Astronautics,Xian 710072 Xian Aerospace Propulsion Institute, Xian 710100
国际会议
The 11th International Space Conference of Pacific-basin Societies(第11届环太平洋国际航天会议)
北京
英文
585-591
2007-05-16（万方平台首次上网日期，不代表论文的发表时间）