Comparative aerodynamic analysis of four tail configurations in unmanned aerial vehicles using computational fluid dynamics

Abstract

The purpose of this study is to evaluate aerodynamic performance, stability and maneuverability of four widely used unmanned aerial vehicle (UAV) tail configurations, i.e. twin tail, V-tail, inverted V-tail and conventional tail under varying flight conditions. Research aims to provide insights into optimizing UAV tail designs for improved aerodynamic efficiency and flight performance. A comprehensive computational fluid dynamics (CFD) analysis was performed on four tail configurations. Simulations were conducted at different altitudes (0 and 5,000 m), airspeeds (36 m/s) and angles of attack (0, 5, 7 and 10°) using the realizable k−ϵ turbulence model to enhance the accuracy of simulations. Key aerodynamic parameters such as drag, lift and pitching moment coefficient were analyzed to assess the effectiveness of each tail configuration. Results indicate that the V-tail configuration demonstrates lower drag compared to other configurations enhancing aerodynamic efficiency. On the other hand, the twin-tail configuration provides superior stability, particularly at high angles of attack. Inverted V-tail and conventional tail configurations showed varying performance characteristics depending on flight conditions, but neither outperformed the V-tail or twin tail in overall performance. This study provides novel insights into the aerodynamic performance of different UAV tail configurations under a range of flight conditions, including variations in altitudes, airspeeds and angles of attack. Findings contribute to a deeper understanding of the relationship between tail design and UAV flight performance, providing valuable guidance for optimizing UAV tail designs to improve both stability and aerodynamic efficiency.