Investigation of flow dynamics over bat type delta wing under oscillation motion

The aim of this study vortex breakdown and separated flow over aircraft play an important role in influencing performance and maneuverability of the aircraft. Vortex breakdown and separated flow originate different flow characteristics over aircraft regarding various angles of attack. This is an undesirable fact for the aircraft. It affects the lifespan of aircraft and maneuverability as well. Vortex which occurs in a various regions of aircraft fuselage having high maneuver capability reduces the maneuvering of aircraft power and its performance. Today, when it comes to the use of UCAV (Unmanned combat air vehicle), the formation of spiral vortex, vortex breakdown over the delta wing in order to increase maneuverability and the interaction with the delta wing surface of the vortex formed after the breakdown must be known and these vortices must be controlled. These are very important in terms of aircraft maneuverability performance. In this study,geometrie for the various angle of attack was investigated experimentally under static condition and sinusoidal motion by using dye visualization and particle image velocimetry technique (PIV). The experimental analysis consists of time averaged velocity vectors, streamline patterns and vorticity contours. In addition, lift and drag coefficients (CL and CD) and pitching moment (PM) were examined by measuring aerodynamic forces of lift and drag forces during static and pitching motion. The experiments were conducted in plan-view planes and it was very close to surface of the delta wing models. Flow structure, development of the vortices, vortex breakdown and aerodynamic coefficients were investigated for different angles of attack Keywords: Delta Wing, Vortex Breakdown, Unmanned Combat Air Vehicle, PI