Lateral inject active vortex control based on low aspect ratio flying wing

In order to improve the lateral control ability of the low aspect ratio flying wing aircraft, a vortex control method is designed which can provide rolling moment for the aircraft, and the effects of leading dissymmetrical vertical injects on flow structure are studied. High precision simulation of the Reynolds average N-S equations and the Spalart-Allmaras torrent model are used to study vortex flows over the low aspect ratio flying wing aircraft with and without leading dissymmetrical edge injects. The results show that the ratio of inject velocity to free flow velocity, injection pressure and attack angle all affect the location of vortex breakdown, vortex intensity and vortex axis position. These factors may cause flow change, which in turn produces dissymmetrical force and moment. Besides producing the rolling moment, vertical inject produces little yawing moment and pitching moment. At the same time the lift and resistance also exhibit little change.