Effects of Streamwise Vortex on Flow Field and Performance of Two-Dimensional Inlet

被引：0
|
作者：
Chen S. [1 ]
Ding M. [1 ]
Wang Q.-C. [1 ]
Zhao Y.-X. [1 ]
Wei F. [1 ]
机构：
[1] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2023年 / 44卷 / 11期
关键词：
Curved compression inlet; Inlet performance; Numerical simulation; Separation zone; Streamwise vortex;
D O I：
10.13675/j.cnki.tjjs.2207096
中图分类号：
学科分类号：
摘要：
The streamwise vortex entering the inlet at supersonic speed will affect its normal operation. In order to solve this problem，a numerical study is carried out at a freestream Mach number of 2.7. The inlet model is a two-dimensional curved compression one，and the vortex generator is a finite span wing. By changing the attack angle and the normal height of wing，the flow field characteristics and the performance of inlet effected by streamwise vortices of two different strength from four different positions are studied. The results show that the two vortices of different strength do not breakdown after the interaction with the inlet shock wave，which are typical weak interactions. Under the influence of streamwise vortex，the separation zone near the entrance of the contraction section shows obvious three-dimensional asymmetric characteristics. In addition，as the streamwise vortex approaches the boundary layer，the separation point of the separation zone gradually moves upstream. Under the influence of the streamwise vortex，the flow coefficient and the total pressure recovery coefficient of the inlet decrease，and the stronger the streamwise vortex is and the closer it is to the boundary layer，the more obvious the adverse effect on the performance of the inlet becomes. In particular，under the conditions of the maximum attack angle and the lowest position，a large-scale separation zone is formed in the upstream of the entrance of the contraction section，which increases the distortion coefficient of the entrance of the contraction section by about 4 times，decreases the flow coefficient by about 6.1%，and decreases the total pressure recovery coefficient by about 17.2%. © 2023 Journal of Propulsion Technology. All rights reserved.
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