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Oscillating behaviour of laminar separation bubble formed on an aerofoil near stall

Published online by Cambridge University Press:  12 October 2016

K. Rinoie  and
N. Takemura
K. Rinoie
Affiliation:
Department of Aeronautics and Astronautics, University of Tokyo, Tokyo, Japan
N. Takemura
Affiliation:
Department of Aeronautics and Astronautics, University of Tokyo, Tokyo, Japan
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Abstract

Laminar separation bubbles formed on NACA 0012 aerofoil near the onset of a stall were investigated to clarify the behaviour of the laminar separation bubble. Measurements were done at a chord Reynolds number of 1·3 × 105. Mean velocity measurements indicate that the long bubble of about 35% chord length is formed at α = 11·5° after the short bubble burst occurred. However, the instantaneous flow visualisation picture indicates that the flow is strongly oscillating at this angle of attack. The phase averaging technique has been applied to analyse this oscillating behaviour. The results indicate that the flow is oscillating between a small separation-reattachment bubble formed near the leading-edge at about a 10% chord length and a large separated region extending over the aerofoil surface. It is suggested that this small separation-reattachment bubble has a similar flow structure to that of the short bubble formed at a lower angle of attack.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1081 , March 2004 , pp. 153 - 163
Copyright
Copyright © Royal Aeronautical Society 2004 

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