Home > Journals and Magazines > Journals > IJAAA > Vol. 4 (2017) > Iss. 3
Abstract
The result of interactions of a wingtip vortex of a half-span wing and vortices generated by a slender reverse delta type add-on device were studied using Particle Image Velocimetry in a closed-loop low-speed wind tunnel. Characteristics of the vortex interactions produced downstream in planes perpendicular to the free stream direction at a mean chord-based Reynolds number, Rec = 2.75×105, are explored in this work. The study reveals that the reverse delta type add-on device considerably reduces the tangential velocity, vorticity and circulation magnitude of the resultant vortex by up to 79.6%, 85.6% and 48.7%, respectively. It was also found that the resultant vortex core radius increased by a factor of 5.63. Using a six component force balance, the reduction in lift and the increase in drag of the half-span wing with the reverse delta type add-on device was recorded to be 2.9% and 14.5%, respectively.
DOI
https://doi.org/10.15394/ijaaa.2017.1178
Scholarly Commons Citation
Altaf, A. (2017). Wingtip Vortex Alleviation Using a Reverse Delta Type Add-on Device. International Journal of Aviation, Aeronautics, and Aerospace, 4(3). https://doi.org/10.15394/ijaaa.2017.1178
