The Investigation on Non-linear Characteristic of Yawing Moment of Twin-tailed Configuration

The twin-tailed configuration, such as F22, is famous for its advantage in the stealth, agilityand maneuverability. However, the variation of yawing moment for this kind of configurationshows non-linear behavior at medium angle of attack combined with sideslip. The main purpose of this paper is to investigate the flow mechanism causing it over a typical twin-tailed configuration by Computational Fluid Dynamics method. Results show thatthe main contribution tothe non-linear behavior of yawing moment is the complex vortices developed from forebody of fuselage and leading-edge of wing acting on the twin- tailed. All the research work was conducted under conditions of freestream velocity 30m/s and 4°sideslip angle.