内流激波边界层干扰非对称特性研究综述  

Review on Asymmetry Characteristics of Shock Wave/Boundary Layer Interactions in Internal Flows

作　　者：孙波[1] 卓长飞[1] Sun Bo;Zhuo Changfei(Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学,江苏南京210094

出　　处：《气动研究与试验》2024年第3期52-59,共8页Aerodynamic Research & Experiment

摘　　要：当内流中(喷管和隔离段)出现激波诱导边界层分离时,可能出现非对称流动现象,即使边界条件是对称的,这一令人费解的现象几十年前便引起研究人员的注意,然而至今对其机理仍未完全揭示。本文对国内外过膨胀喷管和隔离段内非对称激波边界层干扰流动的相关研究进行了综述,总结了非对称流动的典型现象、特征和模式,对近期提出的流动偏转角混合层卷吸模型进行了介绍。When boundary layer separation occurs in the internal flow(nozzles and isolators),asymmetric flow phenomena may occur,even if the boundary conditions are symmetric.This puzzling phenomenon attracted the attention of researchers decades ago,but its mechanism has not yet been fully revealed.This paper provides a review of relevant research on the flow of asymmetric shock/boundary layers in over-expanding nozzles and isolaters both domestically and internationally.It summarizes the typical phenomena,characteristics,and modes of asymmetric flow,and introduces the recently proposed flow deflection angle model based on mixed layer entrainment.

关 键 词：激波边界层干扰 非对称 喷管 激波串 边界层分离 Coanda效应 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]