一种平尾涡流发生器设计和流动控制研究

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攻角下流动特性的应用需求，设计一种涡流发生器，安装在平尾下表面。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，分析飞机在负攻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°，负攻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。

Design and analysis of a vortex generator of horizontal tail

A type of vortex generator is designed for a certain type of mountain transport aircraft, which is installed on the lower surface of the horizontal tail to improve the flow pattern of the horizontal tail at a negative angle of attack and delay the negative stall of the horizontal tail. The flow characteristics and mechanism of the horizontal tail airfoil with and without vortex generator are studied by numerical simulation method, the pitching moment characteristics of the airfoil are analyzed, and the flow control effect of the vertex generator is verified; The vortex generator is installed on the lower surface of the horizontal tail from the wing root to the position of 80% wingspan, and the aerodynamic characteristics of the aircraft with and without the vortex generators are compared and 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.