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Design and Optimization of Winglet Shapes for Cambered Aerofoil
K. Balaji,Apoorva Yadav 한국항공우주학회 2023 International Journal of Aeronautical and Space Sc Vol.24 No.2
The aim of the current research work is to identify the optimum angle for winglets that control the boundary layer by generating vortices over an aerofoil. A cambered aerofoil was used to compare the spiroid, split-scimitar, and blended winglets with modified angles. Numerical analysis in Fluent software using k-omega SST turbulence models with Navier–stokes equations was carried out. The winglets were tested at a Mach number of 0.03. Based on the simulation results, the optimized winglets were fabricated and tested using a subsonic tunnel. The results showed that the optimum angles for the split, blended and spiroid winglets were respectively 140°, 95° and 40°. The NACA 6321 aerofoil at an angle of 95° for blended winglet has provided higher aerodynamic efficiency when compared to other. The optimized angle of the winglet enhanced the aerodynamic performance of the aircraft by controlling the induced drag at different angles of attack.