Numerical Investigation of Winglet Aerodynamics and Dimple Effect of NACA 0017 Airfoil for a Freight Aircraft

Drag reduction is an ever-present challenge within the aeronautical engineering industry. This paper presents two substantial wing modifications: addition of a winglet freighter aircraft and dimpled on NACA 0017 aerofoils. Studies nine (9) different geometries aerofoils were performed against control model aerofoil without any dimple. Computational fluid dynamics (CFD) analysis was using (2) commercial CFD platforms. also explored novel solutions optimisation to mitigate effects drag leading-edge pressure, while increasing effect lift. The optimised performance increased its aerodynamic efficiency. study found that at take-off velocity 82 m/s, winglets decreased pressure by 16.31%, through flow redirection better integration into wake. analysed separation layer appropriate use dimple effect. Increased lift observed aerofoil. Despite low increase in 6% from modifications, resultant L/D ratio highly increased. faced some challenges with validating model. Hence validation approaches taken, other suggested for future studies.