Over time, the need to extend the endurance of fixed-wing UAVs has been a challenge and requirement for the aviation industry. As a result, there are many ongoing researches on how to address this challenge while developing new concepts for an aircraft wing. This paper presents the methodology applied in the design of the wing of a lightweight unmanned aerial vehicle (UAV) that is intended for intelligence and surveillance (ISR) missions. A conceptual design was developed with the aircraft having a hybrid wing for the purpose of improving its structural design. The wing has two spars and thirteen ribs a side with an all-composite structure. Initial calculations were performed theoretically, thereafter, analyzed using the finite element analysis tool.