Description
This book presents the current knowledge on the aerodynamic performances and flow topology above a non-slender delta-winged UAV. As the application of the UAV is emerging, much interest is given into non-slender delta wing configuration for agile and high manoeuvrability applications. The flow characteristic above sharp-edged delta wing is dominated by a vortical flow called as primary vortex. The primary vortex forms due to the flow separation at wing leading-edge and the shear layer roll-up becoming vortex sheet. In this book, the aerodynamic performances of the UAV and the flow topology above the wing is discussed according to three positions of propeller, which are front, middle and rear of a UAV model. The UAV model is tested in low-speed wind tunnel (UTM-LST) at wind velocity of 20 m/s (72 km/h) and 25 m/s (90 km/h). The non-slender wing is recognised from leading-edge sweep angle between 35° to 55°. Two measurement techniques were employed on the wing, namely steady balance data and surface pressure measurement. The flow characteristic above sharp-edged delta wing is dominated by a vortical flow called as primary vortex. The propeller locations on the wing have changed the vortical flow above the wing consequently altered the aerodynamic performances (lift, drag and pitching moment) of the UAV.
