圆形出口内转式进气道流动特征
收稿日期: 2015-01-28
修回日期: 2015-04-19
网络出版日期: 2015-05-05
基金资助
高超声速冲压发动机技术重点实验室开放基金(STSKFKT2014002)
Flow characteristics of an inward turning inlet with circular outlet
Received date: 2015-01-28
Revised date: 2015-04-19
Online published: 2015-05-05
Supported by
Open Fund of Science and Technology on Scramjet Laboratory(STSKFKT2014002)
王卫星 , 郭荣伟 . 圆形出口内转式进气道流动特征[J]. 航空学报, 2016 , 37(2) : 533 -544 . DOI: 10.7527/S1000-6893.2015.0108
The flow characteristics of an inward turning inlet are numerically studied. The results show that at design condition, 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 presents 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.
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