圆形出口内转式进气道流动特征  

Flow characteristics of an inward turning inlet with circular outlet

作　　者：王卫星[1,2] 郭荣伟[1] 

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 [2]中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室,绵阳621000

出　　处：《航空学报》2016年第2期533-544,共12页Acta Aeronautica et Astronautica Sinica

基　　金：高超声速冲压发动机技术重点实验室开放基金(STSKFKT2014002)~~

摘　　要：采用数值仿真的方法研究了内转式进气道的流动特征。研究表明:设计状态在近壁面唇罩激波诱发了二次流,进而发展形成流向涡,造成低能流堆积,隔离段出口流场分布不均,消弱了进气道的抗反压能力。有攻角条件下,口面激波偏离唇罩前缘,激波形态发生改变,激波波面中部展向具有准二维特性,压缩面两侧气流压缩变弱,激波层变薄,出现局部膨胀区;有攻角条件下的无黏流场,在进气道压缩段形成三维流向涡,该流向涡促进高能高速气流向壁面迁移,改善了黏性条件下隔离段出口流场的均匀度。The flow characteristics of an inward turning inlet are numerically studied. The results show that at design condi- tion, the secondary flow near the wall is induced by the cowl shock and the streamwise vortex is generated in isolator, which will cause the flow with low velocity and low total pressure to accumulate. The distribution of the aerodynamic parameters at the isolator outlet is even, which will weaken the back-pressure capacity of inlet. With angle of attack, the compression shock departs the leading edge of cowl lip and the shock wave structure changes. The middle part of the shock wave pres- ents quasi-two-dimensional feature in the span-wise. The shock wave is weak on the two sides of compression surface and the expansion waves occur in local zone. The streamwise vortex presents in the compression section without viscosity with angle of attack, and this streamwise vortex will enhance the transfer of the flow with high total pressure from the core flow region to the wall, so the evenness of flow at the outlet of isolator is improved under viscosity.

关 键 词：流向涡 激波形态 流场特性 内转式进气道 数值仿真 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]