流线追踪Busemann进气道马赫数3.85实验研究  

Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet

作　　者：孙波[1] 张堃元[1] 金志光[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《航空动力学报》2007年第3期396-399,共4页Journal of Aerospace Power

基　　金：国家"八六三"基金项目(2003AA723020)

摘　　要：为了研究流线追踪Busemann进气道在低马赫数来流条件下的起动性能、总体性能以及抗反压能力,对设计马赫数5.3、收缩比CR=5的6°截短后的流线追踪进气道进行了马赫数3.85风洞实验.结果表明:该进气道在马赫数3.85来流条件下能够自起动;进气道流量系数为0.83,出口总压恢复0.78,马赫数2.01,增压比11.92;进气道能够承受的最大反压为34倍的来流静压.A wind-tunnel testing of a streamline traced hypersonic Busemann inlet, with a designed Mach 5.3 and shrinkage ratio CR = 5, was conducted at Mach 3.85 to study its starting and overall performance as well as back-pressure capability below Mach 5.3 conditions. The results show that, the inlet can be started automatically at Mach 3.85; the flow coefficient of inlet is 0. 83, the overall pressure recovery coefficient is 0.78, with a Mach number 2.01 and a compression ratio of 11. 92; the inlet can withstand a maximum backpressure of 34 times static pressure.

关 键 词：航空 航天推进系统 超燃冲压发动机 BUSEMANN进气道 流线追踪 风洞实验 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]