Experimental Investigation on Aircraft Wake Vortex Control by Spoilers

DOI

10.2991/ameii-15.2015.277How to use a DOI?

Keywords

Wake vortex; Spoilers; Particle Image Velocimetry; Rayleigh-Ludwieg Instability; Four-vortex

Abstract

The experimental investigation is mainly to seek an effective method to reduce the strength of aircraft wake vortex which would introduce great hazard to the following flight and threaten the flight safety. The research was carried out in a water-towing tank which equipped with a 2-D Particle Image Velocimetry (PIV) system. By using spoilers attached on the airfoil, the Rayleigh-Ludwieg instability of the wake vortex is activated, leading to the dissipation of the wake vortex in advance. The analysis results given by the PIV system showed that the circulation of the wake vortex was reduced to nearly 40%, as early as in 30 wingspans downstream with suitable settings, instead of more than 100 wingspans for that of a “clean model”. The result could provide reference for designing the low wake vortex airfoils.

Copyright

© 2015, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Jinsheng Liu
PY  - 2015/04
DA  - 2015/04
TI  - Experimental Investigation on Aircraft Wake Vortex Control by Spoilers
BT  - Proceedings of the International Conference on Advances in Mechanical Engineering and Industrial Informatics
PB  - Atlantis Press
SP  - 1505
EP  - 1510
SN  - 2352-5401
UR  - https://doi.org/10.2991/ameii-15.2015.277
DO  - 10.2991/ameii-15.2015.277
ID  - Liu2015/04
ER  -