内收缩比可控的二元高超声速变几何进气道研究  

Research on variable geometry technology of 2-D hypersonic inlet with contract ratio under controlling

作　　者：袁化成[1] 滕健[1] 郭荣伟[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2012年第11期2468-2474,共7页Journal of Aerospace Power

基　　金：南京航空航天大学基本科研业务费专项科研项目(NS2010054);高等学校博士学科点专项科研基金(20103218120009)

摘　　要：提出了一种进气道内收缩比可控、包括唇口后退等几何动作的变几何进气道的设计思路,给出了具体的设计过程及影响因素.据此开展了二元高超声速定、变几何进气道气动方案设计,并进行了细致的数值模拟,给出了进气道气动性能参数随来流马赫数的变化规律,将定、变几何进气道气动性能进行了对比分析,结果显示:设计马赫数下,定、变几何进气道气动性能基本相同;非设计马赫数下,变几何进气道的流量系数明显高于定几何方案,且马赫数越低,两者相差越大.静压比、温升比、总压恢复系数及隔离段出口马赫数则相差不大.Based on the two-dimensional （2 D） fixed hypersonic, a new concept of var- iable geometry hypersonic inlet that the tip moving back off to increase the mass capture ratio was presented. The flow in the hypersonic inlet was analyzed with two-dimensional numeri- cal analyzer, and the inlet performance comparisons were made between the variable geome- try hypersonic inlet and fixed inlet at different Mach numbers of inflow. The results indicate that the performance of the variable geometry inlet in the same as that of the fixed one at de- sign Mach number, and the performance of the variable geometry inlet is better than that of the fixed inlet at non design point. All of them indicate that the variable geometry hyperson- ic inlet is satisfying.

关 键 词：高超声速推进系统 高超进气道 变几何 伸缩唇口 数值模拟 

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]