一种平尾涡流发生器设计和流动控制研究  

Design and Analysis of a Vortex Generator on Horizontal Tail

作　　者：王建 郭高锋 延小超 贾新宇 张文希 WANG Jian;GUO Gaofeng;YAN Xiaochao;JIA Xinyu;ZHANG Wenxi(Aerospace Times Feihong Technology Company Limited,Beijing 100094,China)

机构地区：[1]航天时代飞鸿技术有限公司,北京100094

出　　处：《航空工程进展》2022年第6期116-124,共9页Advances in Aeronautical Science and Engineering

摘　　要：在飞机表面安装涡流发生器,可以起到改善当地流态的作用,达到减阻、增升、降噪、减小旋流畸变的目的,而平尾的气动特性直接影响飞机的飞行安全。基于改善飞机平尾在负迎角下流动特性的应用需求,设计一种安装于平尾下表面的涡流发生器。通过数值模拟方法研究平尾在不安装涡流发生器和安装涡流发生器两种构型下的流动特征和机理,分析飞机在负迎角下的俯仰力矩特性。结果表明:安装涡流发生器的平尾负失速迎角推迟了4°,负迎角下的俯仰力矩拐点推迟了4°左右,拓宽了飞机的飞行边界。The vortex generator installed at the aircraft surface can improve the local flow pattern and achieve the purpose of reducing drag,increasing lift,reducing noise and reducing swirl distortion.The aerodynamic characteristics of the horizontal tail directly affect the flight safety of an aircraft.Based on the application requirement of improving the flow pattern of the horizontal tail at the negative angle of attack,a type of vortex generator is designed,which is installed on the lower surface of the horizontal tail.The flow characteristics and mechanism of the horizontal tail with and without vortex generator are studied by numerical simulation method,and the pitching moment characteristics of the aircraft are analyzed.The calculation results show that the negative stall angle of attack and the pitching moment inflection point of the horizontal tail with the vortex generator is delayed by 4° and the flight boundary of the aircraft is enlarged.

关 键 词：涡流发生器 平尾 气流分离 流动控制 飞行边界 数值计算 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]