Numerical Simulation of the Interaction Between Leading-Edge Vortex and Vertical Tail

The impingement of a streamwise vortex on an aerodynamic surface, such as a fin or tail, can result in efficiency loss, severe unsteady loading, vibration, and adverse stability and control. Such vortices, commonly generated by modern fighter aircraft configurations, are employed to supplement lift and enhance performance and maneuvering capabilities in the high-angle-of-attack subsonic flight regime. In these flow situations, vortex breakdown can occur, leading to buffet of the tail surface with a potential for fatigue induced structural failure. The present investigation considers airflow at a freestream Mach number of 0.2 and root chord Reynolds number of 1.89 X 10 6 past a sharp leading-edge 70.0-deg swept delta wing at an angle of attack of 23.2 deg.