Computational Fluid Dynamics Analysis of Non-slender Cropped Delta Wingsuit

The commercial wingsuit suffers from challenges of low lift and poor aerodynamic efficiency that results in lower endurance and range performance. Cropped delta wings are known for their higher maneuverability. In this study, Gottingen 228 airfoil of aspect ratio 1.05 is used to design a cropped delta wingsuit and Ansys Fluent solver was utilized to solve the Reynolds-averaged Navier–Stokes (RANS) equations with a k − ω turbulence model. In this study the wingsuit is assumed to be flying at a free-stream velocity of 40 m/s. Detailed simulations were recorded at different angles of attack till stall angle to give an insight into the flow dynamics of the wingsuit. Simulations reveal that the wingsuit had a maximum lift coefficient of 2.4 and reached a stall angle of 40°. The wingsuit examined in this study potentially offers 20 and 38% increments in endurance and range in comparison with existing literature. This study paves the path for other researchers to work on improving aerodynamic efficiency of wingsuits.