This paper presents the design, manufacturing, and flight testing of an electric-powered
experimental flying wing unmanned aerial vehicle (UAV). The design process starts with defining
the performance requirements including the stall speed, maximal speed, cruise altitude, absolute
ceiling, and turn radius and speed. The wing loading and associated power loading are obtained
based on the defined performance requirements. The wing area, UAV mass, and power requirements
are determined from the endurance and payload requirements. The power requirement determines
the motor size. Aerodynamics and stability designs are obtained based on the selected airfoil and
obtained wing area. After completing the design, the UAV is manufactured using composite materials.
The UAV is equipped with an AXi 4130/20 kv305 brushless motor and a Pixhawk flight control board.
Its total weight is 8.6 kg. Flight tests were conducted to evaluate the UAV’s performance and dynamic
characteristics and to demonstrate the success of the design.