A discussion session titled “The Effect of Curved Edges on the Aerodynamic Performance of Section slot” was organized by the Department of Aeronautical Engineering on February 18, 2024. The session was presented by Assistant Professor Anmar Hamed Ali. The aim of this session was to study the possibility of reducing the drag coefficient for a wing with slots at a Reynolds number of 1.6×10^6, with angles of attack ranging from 0 to 20 degrees.
The airfoil with a simple slot was manufactured with curved edges in order to improve the aerodynamic performance. The numerical study was evaluated using ANSYS Fluent 21.0, employing the κ-ω SST turbulence model to solve the fully turbulent Navier-Stokes equations. The slot location and dimensions were determined based on previous considerations, with the slot positioned at the 60% chord flap position, oriented at 65 inches and having a slot chord width of 1%.
The edges were curved to ensure smooth flow along the wing surface. The results showed that this approach led to a reduction in the drag coefficient at all angles of attack, with an increase in the lift coefficient at a 214-degree angle and a delay in the stall angle from 15° to 19 degrees. The maximum increase in lift-to-drag ratio was 3.9 times that of the solid wing at a 17-degree angle of attack.
These findings are utilized to enhance the design and improve the aerodynamic performance of the wing under various conditions. The discussion session will focus on these results and potential applications. The official email address of the lecturer is [email protected].
