亚声速S弯进气道研究的新进展  

Recent Progress in Subsonic S-Shaped Inlets

作　　者：黄河峡 孙姝[3] 于航 谭慧俊 林正康 李子杰 汪昆 HUANG He-xia;SUN Shu;YU Hang;TAN Hui-jun;LIN Zheng-kang;LI Zi-jie;WANG Kun(Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;School of Aerospace Engineering,Tsinghua University,Beijing 100084,China;College of Civil Aviation,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

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,江苏南京210016 [2]清华大学航天航空学院,北京100084 [3]南京航空航天大学民航/飞行学院,江苏南京210016

出　　处：《推进技术》2020年第12期2641-2658,共18页Journal of Propulsion Technology

基　　金：国家自然科学基金(51906104,11772156,11532007);江苏省自然科学基金(BK20190385);航空动力基金(6141B09050387);江苏省“333”工程资助项目(BRA2018031)。

摘　　要：当前推进系统与飞行器正朝着高度融合的方向发展,超紧凑蛇形进气道和边界层吸入式进气道则是实现两者融合的关键之一。本文综述了近十余年来国内外关于这两类亚声速S弯进气道的最新研究进展。受显著横向压力梯度、流向逆压梯度的作用,两类进气道内部均存在明显的流动分离,并诱发了大尺度的流向对涡和显著的出口总压畸变。为此,研究者发展了被动式、主动式、混合式等多种流动控制方法,可在不显著增加总压损失的前提下,大幅降低设计工况时出口周向总压畸变。并且,已经建立可适应任意异形进口的S弯进气道气动型面通用设计方法。最后,已有的CFD方法可以较为准确地预测AIP截面平均总压恢复系数,但畸变指数偏差较大。Currently the propulsion system and aircraft tend to be highly integrated,the ultra-compact serpentine inlet and boundary layer ingesting inlet are the keys to realize the fusion.This article reviews the latest research progress of the two types of subsonic S-shaped inlets in related fields at home and abroad in recent ten years.Remarkable flow separation,induced by the transverse and streamwise adverse pressure gradients,are generated within the two types of inlets,forming pairs of large scale vortices and apparent total pressure distortion at outlet.Therefore,researchers have developed a variety of passive,active and hybrid flow control methods,which can lower the distortion index of circumferential total pressure without significant increasing of the total pressure loss in the design condition.Moreover,a general design method for the aerodynamic profile of the Sshaped inlets has been established,which can be adopt to any special entrance shape.Finally,the current CFD methods can accurately predict the time-averaged total pressure recovery coefficient at AIP(Aerodynamic Interface Plane),but the predicted distortion index deviation is large.

关 键 词：进气道 边界层 流动分离 旋涡 流动控制 综述 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]