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The scope of this project was the design and development of a fixed-wing UAV for Teknofast with the maximum take-off mass of 12 kg. In the design stage, it was necessary to take into account the weight and size of all equipment on board to obtain an appropriate center of gravity position and stable aerodynamic characteristics. To ensure that the UAV does not fail structurally while maneuvering, the wings were designed to resist the minimum load factor of 6G. A common airfoil was selected and studied to find out the aerodynamic characteristics of the wing, such as the lift coefficient (CL), drag coefficient (CD), etc. The angle of attack and Reynolds number at the expected speed were considered in order to define those characteristics. The geometrical shape of the fuselage also had to be considered from the point of view of aerodynamics; therefore, the profile similar to the chosen airfoil was used.