Reduction of Wingtip Vortex from Suction at Wingtip

Sangram Keshari Samal, P. K. Dash


Wingtip vortices are strongly associated with induced drag for a three-dimensional wing. So it is important to study the characteristics of wingtip vortices in order to reduce the induced drag. In this paper, numerical simulations of the tip vortices for an unswept and untwisted rectangular wing (NACA 0012) are carried out at a geometric angle of attack 10° using the commercial Computational Fluid Dynamics code (Fluent), and numerical results are compared with the low speed wind tunnel experimental measurements carried out at NASA. The numerical results that were obtained by using CFD code show a good agreement with the experimental results. This has been done for the purpose of validation so that the code can be applied with confidence for modified configuration. Few different configurations have been evaluated computationally to explore their potential to reduce the wing tip vortex. It is shown by numerical calculation that the strength of the vorticity is significantly reduced when suction is applied on the wing tip and along a slot on the bottom surface near to trailing edge.

Full Text:




  • There are currently no refbacks.

Copyright (c)

Mechanical Engineering Research   ISSN 1927-0607 (Print)   ISSN 1927-0615 (Online)   Email:

Copyright © Canadian Center of Science and Education

To make sure that you can receive messages from us, please add the '' domain to your e-mail 'safe list'. If you do not receive e-mail in your 'inbox', check your 'bulk mail' or 'junk mail' folders.


lockss_logo_2_120 images_120. proquest_logo_120