一种紧凑无人机进气道设计和流动控制研究  

Design and Analysis of a Compact UAV Duct and Flow Control Using Vortex Generator

作　　者：赵霞[1] 朱宇[1] 

机构地区：[1]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《飞机设计》2012年第6期1-5,14,共6页Aircraft Design

摘　　要：在满足对发动机风扇全遮挡的前提下,提出一种双"S"弯紧凑进气道的设计方案,通过CFD计算和风洞试验验证,进气道出口流场基本满足发动机要求。另外,对采用涡流发生器方法控制流动分离的备选方案进行了试验研究,证实该方法能够降低发动机进口流场的稳态周向畸变。A compact inlet s-duct was successfully designed through intensive application of CFD,the wind tunnel tests show that meet aircraft and engine target.A standby design of controlling flow separation by vortex generators was also tested,this device can effectively reduce steady state circumferential distortion of engine entrance flowfield.

关 键 词：进气道 风洞试验 流场畸变 涡流发生器 

分 类 号：V228.71[航空宇航科学与技术—飞行器设计]