Low-Speed Wind Tunnel Tests on a Multi-Configurable Planform UCAV Model

The ever-growing demand for uninhabited combat aerial vehicles (UCAVs) in military applications necessitates higher survivability due to the nature of hostile conditions, and this can be achieved by increasing the UCAV maneuverability. The present work was motivated by the potential of a multi-configurable UCAV planform that avoids gaps using smooth deflected wingtips. Experimental analysis was performed to obtain the low-speed aerodynamic characteristics of a lambda UCAV wing model with various deflected wingtips. The low-speed wind tunnel tests were performed at the de Havilland closed return atmospheric low-speed wind tunnel facility at the University of Glasgow. Various wingtip deflections, such as symmetric wingtip positively deflected up and negatively deflected down, were considered for the testing. In addition, an asymmetrical configuration with one wingtip deflected positively and negatively, whereas the other wingtip has no deflection. The present study demonstrated the potential of wingtip deflection models that allow for customizable aerodynamic performance and stability, which can improve UCAV maneuverability during flight.