抽吸对高超声速进气道起动能力的影响  

Effect of suction on starting of hypersonic inlet

作　　者：袁化成[1] 梁德旺[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：《推进技术》2006年第6期525-528,共4页Journal of Propulsion Technology

基　　金：国家"八六三"基金项目(2004AA723020)

摘　　要：对在不同抽吸开孔率下,某典型高超声速二元进气道二维流场进行了数值模拟,给出了高超声速进气道性能参数随抽吸开孔率的变化规律,研究了抽吸对高超声速进气道起动和再起动能力的影响,发现抽吸可以有效地降低进气道的起动马赫数,改善进气道的流动性能,提高进气道的总压恢复系数,但降低了压比,且开孔率越大,上述变化越明显;同时还发现抽吸能够减小高超声速进气道的迟滞回路曲线,大大降低进气道再起动马赫数,改善进气道再起动过程中的超压、超温问题。The flow in a typical 2D hypersonic inlet with and without suction was analyzed and comparied to reveal the effect of suction on the starting of hypersonic inlet. The flow characteristics of a 2D hypersonic inlet at different inflow Mach numbers were discussed. The results show that the inlet with suction can start easily and its total pressure recovery was higher than those without suction. But its pressure ratio was much lower. The change described is more obvious with increase of suction porosity . Starting and restarting Mach number of the inlet with suction is much less than those without suction.

关 键 词：高超声速进气道 抽吸 起动 数值仿真 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]