FLOW SEPARATION STABILIZATION IN FIXED WING UNMANNED AERIAL VEHICLE MODEL

This paper investigates the use of passive flow control methods for stabilizing flow separation on the wings of a fixed-wing unmanned aerial vehicle(UAV).Flow separation can significantly affect the performance and stability of the aircraft, particularly during low-speed flight and high angle of attack manoeuvres. Our aim of the project is to design a wing with vortex generator on the upper surface of the wing and analyse the results using design software CFD.The proposed approach involves the use of vortex generators and boundary layer fences to manipulate the airflow over the wing surface, enhancing its stability and reducing the likelihood of flow separation. The effects of these flow control devices on the aerodynamic performance are evaluated through a combination of wind tunnel testing and computational fluid dynamics simulations. The results demonstrate that the implementation of vortex generators and boundary layer fences can effectively stabilize flow separation and improve the UAV aerodynamic performance. The use of these passive flow control methods can significantly reduce drag and improve lift, making the aircraft more efficient and manoeuvrable during low-speed flight and high angle of attack manoeuvres. Overall, this provides a valuable insight into the potential benefits of passive flow control methods for UAVs, particularly in applications that require stable and efficient flight performance. with maximum and designed by CATIA V5 and analysed by Ansys.