关键词: 高超声速进气道, 双燃烧室发动机, 非设计点, 再起动

Abstract:

In this paper, both experimental and computational investigation are conducted on the hypersonic inlet for ramjet module of the dual-coubustion ramjets (DCR) to obtain the off-design performance and to analyze the internal flow pattern and the restarting characteristics. The results show that while operating at the critical state of Mach 4, at the exit section of the inlet the total pressure coefficient is 0.425, the average Mach number is 0.519 and the back pressure is 56.52 times of the free stream pressure. The corresponding critical performance parameters of Mach 5 are 0.240, 0.486 and 125.94 respectively. The mass flow ratio of the inlet decreases substantially at off-design conditions with a value of 0.813 at Mach 5 and a value of 0.593 at Mach 4. Therefore, it is an urgent task to improve the off-design performance of hypersonic inlets. The studied inlet has the ability of self-starting at Mach 4.

Key words: hypersonic , inlet,  , dual-combustion , ramjet,  , offdesign , condition,  , self-starting