Today, with the rapid advancement of technology, new concepts and technologies are entering our lives. In these unmanned aerial vehicles, the effect of designing the wing and tail design for the purpose of use of the unmanned aerial vehicle on the aerodynamic and stabilization structures and has been investigated. The results obtained encode a significant influence on the aerodynamic and stabilization structures of the wing and tail design. It is anticipated that by changing the wing and tail profile design, an effective unmanned aerial vehicle that fulfills the requirements of the desired purpose will be made. The published profile selections analyze, and calculations were made. The points that were considered in the wings and tails while choosing the profiles were examined and compared. In the XFLR5 program, the analysis of the profiles and the analysis of the most appropriate profile results were made by examining the Cl, Cp, Cd, Cm, Alpha, wind, and pressure tests of the 3-dimensional structures. The most suitable profiles were selected for the sash and profiles made and researches were carried out on them. In the studies carried out, attention was paid to the wind flow in the highest value of Cl value in the blades and the choices were made considering the producibility of the profile types. In the studies carried out, the tail profile of the unmanned aerial vehicle has been investigated in this regard, so that the laminar flow coming from the wing can come correctly and not hump momentum. The most suitable structure for the experimental common wing was found to be NACA-4412. NACA-0009 Profile the most suitable profile was selected for the queue. In the experiments performed, it was concluded that wing, tail structures, and maturity were zero cm and can be used with a flow laminator in 3D XFLR5 tests.
Anahtar Kelimeler: Unmanned aerial vehicle (IHA), Profile selection, Airfoil tools, Tail, Analysis
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