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Dynamics of the wing-tip vortex in the near field of a NACA 0012 aerofoil

Published online by Cambridge University Press:  27 January 2016

C. del Pino ,
J.M. López-Alonso ,
L. Parras  and
R. Fernandez-Feria
J.M. López-Alonso
Affiliation:
University of Málaga, Málaga, Spain
L. Parras
Affiliation:
University of Málaga, Málaga, Spain
R. Fernandez-Feria
Affiliation:
University of Málaga, Málaga, Spain
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Abstract

The dynamics of the wing tip vortex in the near-field of a NACA 0012 aerofoil has been analysed by means of flow visualisations in a water tunnel. Different axial distances near the wing up to four chords, Reynolds numbers up to 42,000 and three angles-of-attack are studied to characterise the behaviour of the vortex meandering. The spatio-temporal vortex centre positions show distorted elliptical shapes in a (x,y)-plane. The Reynolds number has no significant influence on the axial evolution of the meandering amplitude. In addition, the flow visualisations obtained with a low speed camera are analysed by the singular value or proper orthogonal decomposition. Thus, the most energetic displacement modes are obtained. The frequency associated to these modes is computed by FFT. In all the cases studied, our results show that the most unstable mode corresponds to the azimuthal wavenumber |n| = 1 in the so-called Kelvin helical modes and the frequency is lower or close to 1Hz.

Type
Research Article
Information
The Aeronautical Journal , Volume 115 , Issue 1166 , April 2011 , pp. 229 - 239
Copyright
Copyright © Royal Aeronautical Society 2011 

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