Design and Analysis of a Vortex Generator on Horizontal Tail

Abstract

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.

Keywords

• vortex generator(vg)
• horizontal tail
• flow separation
• flow control
• flight boundary
• numerical simulation