Get 20M+ Full-Text Papers For Less Than $1.50/day. Start a 14-Day Trial for You or Your Team.

Learn More →

Design and Optimization of Winglet Shapes for Cambered Aerofoil

Design and Optimization of Winglet Shapes for Cambered Aerofoil 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. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical and Space Sciences Springer Journals

Design and Optimization of Winglet Shapes for Cambered Aerofoil

Download PDF
8 pages

Loading next page...
 
/lp/springer-journals/design-and-optimization-of-winglet-shapes-for-cambered-aerofoil-E0RjYpo72G

References (24)

Publisher
Springer Journals
Copyright
Copyright © The Author(s), under exclusive licence to The Korean Society for Aeronautical & Space Sciences 2022. Springer Nature or its licensor (e.g. a society or other partner) holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-022-00544-6
Publisher site
See Article on Publisher Site

Abstract

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.

Journal

International Journal of Aeronautical and Space Sciences – Springer Journals

Published: Apr 1, 2023

Keywords: Drag coefficient; Induced drag; Lift coefficient; Vortices; Winglets

There are no references for this article.