Experimental investigation of the influence of a reverse delta type add-on device on the flap-tip vortex of a wing

• Main Authors: Altaf, Afaq, Thong, Tan Boon, Omar, Ashraf Ali, Asrar, Waqar
• Format: Conference or Workshop Item
• Language: English; English
• Published: IOP Publishing 2017
• Subjects: TL500 Aeronautics
• Online Access: http://irep.iium.edu.my/56983/8/56983-edited.pdf; http://irep.iium.edu.my/56983/7/56983-Experimental%20Investigation%20of%20the%20Influence%20of%20a%20Reverse%20Delta%20Type%20Add-on%20Device%20on%20the%20Flap-tip%20Vortex%20of%20a%20Wing-SCOPUS.pdf; http://irep.iium.edu.my/56983/; http://iopscience.iop.org/article/10.1088/1757-899X/184/1/012002/pdf

Particle Image Velocimetry was used in a low speed wind tunnel to investigate the effect of interactions of vortices produced by an outboard flap-tip of a half wing (NACA 23012 in landing configuration) and a slender reverse delta type add-on device, placed in the proximity of the outboard flap-tip, on the upper surface of the half wing. This work investigates the characteristics of the vortex interactions generated downstream in planes perpendicular to the free stream direction at a chord-based Reynolds number of Re c =2.74×105 . It was found that the add-on device significantly reduces the tangential velocity magnitude and enlarges the vortex core of the resultant vortex by up to 36.1% and 36.8%, respectively.