Aerodynamic and Stability Analysis of a VTOL Blended-Wing Body UAS with Experimental Flight Testing

This study presents the study of aerodynamic properties of a blended wing body (BWB) unmanned aerial system (UAS) with vertical takeoff and landing (VTOL) capabilities. The UAS’s innovative design allows for VTOL and hovering capabilities similar to multi-copter drones, as well as cruise flying efficiency comparable to fixed-wing aircraft. The generation of lift by the complete airframe and the decrease of drag in the wing–body attachment are the major benefits of the BWB concept. Based on the calculated wing parameters, a baseline design was developed using XFLR5, and trade studies were performed to obtain the optimum tradeoff between aerodynamic performance and overall stability. The final CAD model was developed using CATIA and Planemaker, followed by flight simulations in X-Plane 11. After evaluating performance and stability characteristics, the prototype was fabricated and integrated with electronic subsystems. Flight tests were carried out and flight data were analyzed to study the UAS’s response to a planned mission. Analysis of flight data confirmed successful VTOL-to-fixed-wing transitions exhibiting satisfactory performance and stability characteristics, demonstrating the potential of the UAS for aerial experiments, reconnaissance, and environmental monitoring missions.