In the present thesis, an unmanned aerial vehicle (UAV) is designed in terms of wing geometry and control surfaces available on it to represent a wide range of civil aircraft. However, unlike civil jet aircraft, the UAV will have a V-Tail. The wing airfoil is chosen considering the UAV’s flight regime. The airfoil’s choice is done through two-dimensional CFD analysis at low to moderate Reynolds numbers. Due to the low computational power available, the analyses are done only for reduced angles of attack, which are representative of the flight condition of the cruise, and where the problem can be considered in the first approximation as steady-state.