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Numerical Study in Wing Tip Vortex for a Modified Commercial Boeing Aircraft

[+] Author Affiliations
Ricardo Hernandez-Rivera, Abel Hernandez-Guerrero, Cuauhtemoc Rubio-Arana

Universidad de Guanajuato, Salamanca, Guanajuato, México

Raul Lesso-Arroyo

Tecnológico de Celaya, Celaya, Guanajuato, México

Paper No. IMECE2008-68149, pp. 349-356; 8 pages
doi:10.1115/IMECE2008-68149
From:
  • ASME 2008 International Mechanical Engineering Congress and Exposition
  • Volume 10: Heat Transfer, Fluid Flows, and Thermal Systems, Parts A, B, and C
  • Boston, Massachusetts, USA, October 31–November 6, 2008
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4871-5 | eISBN: 978-0-7918-3840-2
  • Copyright © 2008 by ASME

abstract

Recent studies have shown that the use of winglets in aircrafts wing tips have been able to reduce fuel consumption by reducing the lift-induced drag caused by wing tip vortex. This paper presents a 3-D numerical study to analyze the drag and lift forces, and the behavior of the vortexes generated in the wing tips from a modified commercial Boeing aircraft 767-300/ER. This type of aircraft does not contain winglets to control the wing tip vortex, therefore, the aerodynamic effects were analyzed adding two models of winglets to the wing tip. The first one is the vortex diffuser winglet and the second one is the tip fence winglet. The analyses were made for steady state and compressible flow, for a constant Mach number. The results show that the vortex diffuser winglet gives the best results, reducing the core velocity of the wing tip vortex up to 19%, the total drag force of the aircraft up to 3.6% and it leads to a lift increase of up to 2.4% with respect to the original aircraft without winglets.

Copyright © 2008 by ASME

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