Numerical Study of the Effect of the Trailing-Edge Devices (Gurney Flap and Divergent Trailing-edge Flap) on the Aerodynamic Characteristics of an Airfoil in Transonic Flow for Drone Applications

Abstract

The primary objective of this research was to examine how the inclusion of mini Trailing-edge devices (referred to as mini TEDs) impacts the aerodynamic properties of the RAE-2822 airfoil. Utilizing ANSYS Fluent software, we conducted numerical simulations to analyze the behavior of compressible flow around the airfoil, specifically at a Mach number (Ma) of 0.73, while varying the angles of attack. The mini TEDs employed in our simulations com - prised a Gurney flap and a divergent trailing-edge. Our findings demonstrate that incorporating these mini TEDs at the trailing-edge leads to a noteworthy increase in the lift coefficient (CL) and drag coefficient (CD). However, it is worth noting that this enhancement resulted in an improved lift-to-drag ratio for the airfoil for specific angles of attack. These outcomes underscore the potential advantages of employing mini TEDs to enhance aerodynamic performance, especially in aerospace drone applications.