Effect of a directionally porous wing tip on tip vortex
This paper presents an experimental study of the effect of a directionally porous wing tip on the tip vortex using particle image velocimetry (PIV) on a half wing model with NACA 653218 as its airfoil section. Four different configurations of the directionally porous wing tip are tested. The vorte...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Journal of Applied Fluid Mechanics
2020
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/76419/ http://irep.iium.edu.my/76419/ http://irep.iium.edu.my/76419/ http://irep.iium.edu.my/76419/3/29738_090219035335.pdf |
| Summary: | This paper presents an experimental study of the effect of a directionally porous wing tip on the tip vortex using
particle image velocimetry (PIV) on a half wing model with NACA 653218 as its airfoil section. Four different
configurations of the directionally porous wing tip are tested. The vortex generated by the wing tips are
examined at four different measuring planes downstream perpendicular to the flow axis. The flow field over
the porous wing tip surface along the streamwise direction is obtained as well to understand the effects of the
porosity on the flow which in the end affects the vortex downstream. Furthermore, the aerodynamic
performance of all different configurations is compared to study their effects on the aerodynamic coefficients
of the wing. The results show a high reduction in vorticity, up to 90%; tangential velocity reduction up to 67%
and a significant reduction in vortex circulation in the near-far field. Effect on the lift to drag ratio is
up to 20 %. |
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