The Influence of Leading Edge Vortex Generators on the Efficiency of Lateral Control Surfaces

Abstract

An alternative approach for increasing the flight control efficiency by means of volumetric vortex generators at leading edges of lifting surfaces of the unmanned aerial vehicles is presented. The arrangement of leading edge vortex generators in the form of a vortex slat changes the conventional model of flow around wing into an optimally organized longitudinal spiral slipstream. This eliminates the global flow separation, increases the critical angle of attack, and improves stability characteristics of a wing. The generated longitudinal vortices reach the trailing edge, eliminating flow separation from control surfaces at critical and post-critical angles of attack. This method increases the efficiency of control systems in flight modes at low Reynolds numbers and large angles of attack, which improves controllability, increases the level of flight safety, and facilitates the development of adaptive unmanned aerial vehicles control systems.