进气道内激波 /边界层干扰及控制研究进展

doi:10.13675/j.cnki.tjjs.190376

推进技术 ›› 2020, Vol. 41 ›› Issue (2): 241-259.DOI: 10.13675/j.cnki.tjjs.190376

• 综述 • 下一篇

进气道内激波 /边界层干扰及控制研究进展

张悦¹,谭慧俊¹,王子运¹,李鑫¹,郭赟杰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，江苏南京 210016

发布日期:2021-08-15
作者简介:张悦，博士，副教授，研究领域为内流空气动力学。E-mail： y.zhang@nuaa.edu.cn
基金资助:
国家自然科学基金（11532007；51806102）；中国博士后科学基金（2016M600412）；江苏省高校优势学科建设工程资助项目。

Progress of Shock Wave/Boundary Layer Interactionand Its Control in Inlet

Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Published:2021-08-15

摘要/Abstract

摘要： 进气道作为高速航空航天飞行器的重要气动部件，对飞行器的气动力特性、结构重量、隐身性能等有显著影响。激波/边界层干扰现象是高速进气道内普遍存在的一类流动现象，对进气道的性能有突出的影响。发生于进气道内的激波/边界层干扰现象主要可分为正激波/边界层干扰、斜激波/边界层干扰以及三维激波/边界层干扰几类，由于受到侧壁壁面和进气道内背景波系的影响，这些干扰现象偏离了传统基于简化模型的研究结果，具有显著的耦合干扰特征，干扰区间内三维特征明显。概述了发生于进气道内的激波/边界层干扰特性及相关研究进展，并对目前进气道内激波/边界层干扰现象的控制方法进行了总结。

关键词: 进气道;激波;边界层干扰;流动控制

Abstract: Inlet is an important aerodynamic component of a high speed aeronautical and aerospace vehicle. The aerodynamic performance, weight and stealth performance of the vehicle is largely dictated by the inlet. Shock/boundary layer interaction is a common phenomenon in a high speed inlet and plays an important role in the inlet performance. The shock/boundary layer interaction in inlets can be classified into normal shock/boundary layer interaction, oblique shock/boundary layer interaction and three-dimensional shock/boundary layer interaction. Due to the effects of sidewall and complex background waves, the shock/boundary layer interaction in the inlet embodies significant three-dimensional character and remarkable coupling effect which make its prediction go beyond the scope of current shock/boundary layer interaction theory. A brief summary on related research of shock/boundary layer interaction and its control methods in high speed inlets was given.

Key words: Inlet;Shock wave;Boundary layer interaction;Flow control

张悦,谭慧俊,王子运,李鑫,郭赟杰. 进气道内激波 /边界层干扰及控制研究进展[J]. 推进技术, 2020, 41(2): 241-259.

ZHANG Yue¹,TAN Hui-jun¹,WANG Zi-yun¹,LI Xin¹,GUO Yun-jie¹. Progress of Shock Wave/Boundary Layer Interactionand Its Control in Inlet[J]. Journal of Propulsion Technology, 2020, 41(2): 241-259.

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进气道内激波 /边界层干扰及控制研究进展

Progress of Shock Wave/Boundary Layer Interactionand Its Control in Inlet

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