CFD analysis of variable geometric angle winglets

• Published in: Aircraft engineering Vol. 94; no. 2; pp. 289 - 301
• Main Authors: Kazim, Ali Hussain, Malik, Abdullah Hamid, Ali, Hammad, Raza, Muhammad Usman, Khan, Awais Ahmad, Aized, Tauseef, Shabbir, Aqsa
• Format: Journal Article
• Language: English
• Published: Bradford Emerald Publishing Limited 07.01.2022; Emerald Group Publishing Limited
• Subjects: Aeronautics; Aircraft; Alternations; Angle of attack; Animal feathers; Birds; Computational fluid dynamics; Configuration management; Design; Drag reduction; Energy consumption; Experiments; Induced drag; Mach number; Mathematical models; Sweep angle; Visualization; Vortices; Wing tips; Winglets; Variable toe angles; Computational fluid dynamics; Lift-induced drag; Winglets
• ISSN: 1748-8842; 1758-4213
• DOI: 10.1108/AEAT-10-2020-0241

Purpose Winglets play a major role in saving fuel costs because they reduce the lift-induced drag formed at the wingtips. The purpose of this paper is to obtain the best orientation of the winglet for the Office National d’Etudes et de Recherches Aérospatiales (ONERA) M6 wing at Mach number 0.84 in terms of lift to drag ratio. Design/methodology/approach A computational fluid dynamics analysis of the wing-winglet configuration based on the ONERA M6 airfoil on drag reduction for different attack angles at Mach 0.84 was performed using analysis of systems Fluent. First, the best values of cant and sweep angles in terms of aerodynamic performance were selected by performing simulations. The analysis included cant angle values of 30°, 40°, 45°, 55°, 60°, 70° and 75°, while for the sweep angles 35°, 45°, 55°, 65° and 75° angles were used. The aerodynamic performance was measured in terms of the obtained lift to drag ratios. Findings The results showed that slight alternations in the winglet configuration can improve aerodynamic performance for various attack angles. The best lift to drag ratio for the winglet was achieved at a cant angle of 30° and a sweep angle of 65°, which caused a 5.33% increase in the lift to drag ratio. The toe-out angle winglets as compared to the toe-in angles caused the lift to drag ratio to increase because of more attached flow at its surface. The maximum value of the lift to drag ratio was obtained with a toe-out angle (−5°) at an angle of attack 3° which was 2.53% greater than the zero-toed angle winglet. Originality/value This work is relatively unique because the cant, sweep and toe angles were analyzed altogether and led to a significant reduction in drag as compared to wing without winglet. The wing model was compared with the results provided by National Aeronautics and Space Administration so this validated the simulation for different wing-winglet configurations.