一种锯齿状唇口超声速轴对称进气道特性  

Characteristics of a supersonic axisymmetric inlet with saw tooth lip

作　　者：郭金默 谢旅荣 李晓驰 汪昆 胡蓉 GUO Jinmo;XIE Lürong;LI Xiaochi;WANG Kun;HU Rong(Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏省航空动力系统重点实验室,南京210016

出　　处：《航空动力学报》2021年第2期264-274,共11页Journal of Aerospace Power

摘　　要：为探究锯齿状唇口对进气道气动特性的影响,完成了一种常规唇口轴对称进气道设计后,在保持其他基本构型参数和几何特征不变的基础上,通过对其唇口进行剪切构造出锯齿状切口,得到了一种锯齿状唇口超声速轴对称进气道,采用标准k-ε湍流模型对比分析了该进气道与原始型面进气道的气动特性。结果表明:锯齿状唇口进气道通过唇口溢流牺牲流量系数获得较低的自起动马赫数,并提高了总压恢复系数,同时也使喉道马赫数有所增大;设计状态及高来流马赫数条件下,内通道壁面存在分离包横向迁移现象,流动分离情况较原始进气道有所改善。In order to investigate the effects of saw tooth lips on the aerodynamic characteristics of the inlet, after completing a conventional axisymmetric inlet design, the lip was sheared to saw teeth, and a supersonic axisymmetric inlet with saw teeth was obtained on the basis of keeping other basic configuration parameters and geometric characteristics unchanged. The standard turbulence model was applied and the aerodynamic characteristics were analyzed with/without saw teeth. The results showed that: the reduction of area of the cowl lip could decrease the self-starting Mach number of the inlet effectively at price of sacrificing some mass flow. Meanwhile, the total pressure recovery and throat Mach number increased.Under the design state and at high inflow Mach number, there was a phenomenon of lateral migration of separation bubble in inner channel, and the flow separation was better than that of the primary inlet.

关 键 词：轴对称进气道 锯齿状唇口 流场特性 自起动马赫数 流量系数 总压恢复系数 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]