Experimental investigation of the influence of a reverse delta type add-on device on the flap-tip vortex of a wing
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-t...
| Main Authors: | , , , |
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| Format: | Conference or Workshop Item |
| Language: | English English |
| Published: |
IOP Publishing
2017
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/56983/ http://irep.iium.edu.my/56983/ http://irep.iium.edu.my/56983/ 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 |
| Summary: | 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. |
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