Aerodynamics analisys of the wingtip fence effect on UAV wing

Winglets have an important effect in the use of aircraft and of unmanned aerial vehicle (UAV). The expected effect in winglet usage is the increase of the lift coefficient and the decrease of the drag coefficient. These aspects play a very important role in determining aerodynamic performance. Many researches have been done in order to determine the most effective winglet designs to further explore the effects on aircraft and unmanned aerial vehicle (UAV). Based on that fact, in this study the use of winglet on UAV is discussed. This research has been conducted using a simulation software with turbulent model k-ω SST. The freestream velocity used is 10 m / s (Re=2.3 × 10⁴) with an angle of attack (α) = 0^o, 2^o, 4^o, 6^o, 8^o, 10^o,12^o, 15^o, 16^o, 17^o and 19^o . Model specimens are airfoils Eppler 562 with and without winglet. Winglet used in this study are wingtip fences with forward and rearward configuration. From the research, it has been found that the addition of winglet can minimize vorticity magnitude behind the wing especially forward wingtip fence. Forward wingtip fence results in a smaller vorticity area than plain wing and rearward wingtip fence although the vorticities increase with the increase of the angles of attack. In addition, the forward wingtip fence can prevent the formation of tip vortex better than the rearward one.