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The effect of wing planform shape on dynamic stall

Part of: 75 year anniversary of Aeronautical Engineering at Glasgow University

Published online by Cambridge University Press:  04 July 2016

F. N. Coton ,
R. A. McD. Galbraith  and
R. B. Green
F. N. Coton
Affiliation:
Department of Aerospace Engineering University of Glasgow Glasgow, UK
R. A. McD. Galbraith
Affiliation:
Department of Aerospace Engineering University of Glasgow Glasgow, UK
R. B. Green
Affiliation:
Department of Aerospace Engineering University of Glasgow Glasgow, UK
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Abstract

This paper examines the dynamic stalling of three wing planforms and characterises the main features of the stalling process in each case. The particular data were obtained during a three year research programme in the Department of Aerospace Engineering, University of Glasgow to collect high-resolution unsteady pressure data on the dynamic stalling characteristics of finite wing planforms. In this study, which was motivated by the pressing need for a greater understanding of the strongly three-dimensional effects in the tip region of helicopter rotors, the three wing planforms considered were a straight rectangular wing, a rectangular wing with swept tips and a delta wing. The initial test programme was followed by a further three years of detailed analysis and interpretation of the test data. Results from this analysis are presented in the present paper for cases in which the wings were subject to ramp motions.

Type
Research Article
Information
The Aeronautical Journal , Volume 105 , Issue 1045 , March 2001 , pp. 151 - 159
Copyright
Copyright © Royal Aeronautical Society 2001 

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