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An experimental study of dynamic stall on a finite wing

Published online by Cambridge University Press:  04 July 2016

F. N. Coton  and
R. A. McD. Galbraith
F. N. Coton
Affiliation:
Department of Aerospace EngineeringUniversity of GlasgowGlasgow, UK
R. A. McD. Galbraith
Affiliation:
Department of Aerospace EngineeringUniversity of GlasgowGlasgow, UK
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Abstract

This paper examines the dynamic stalling of a finite wing of aspect ratio 3·0 when subject to constant pitch motions up to and beyond stall. In particular, unsteady surface pressure data were obtained at 192 locations on the wing surface and these were then analysed to provide information on the nature and phasing of dynamic stall events in both the chordwise and spanwise directions. It was also possible to obtain sectional force and moment coefficients by integration of the pressures measured on specific chordal arrays. This provided valuable insight into the load distribution on the wing throughout the range of motion. On this basis, it was established that the wing loading distribution was consistent with conventional understanding of steady wing loading up to the incidence at which the dynamic stall vortex was initiated. Beyond this point, the formation and subsequent convection of the vortex structure was found to be strongly three-dimensional but, nevertheless, exhibited many of the features of two-dimensional dynamic stall.

Type
Research Article
Information
The Aeronautical Journal , Volume 103 , Issue 1023 , May 1999 , pp. 229 - 236
Copyright
Copyright © Royal Aeronautical Society 1999 

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