Analysis of model rotor blade pressures during parallel interaction with twin vortices

Coton, F.N., Galbraith, R.A.M. and Green, R.B. (2005) Analysis of model rotor blade pressures during parallel interaction with twin vortices. Journal of Aircraft, 42(6), pp. 1553-1565.

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Abstract

This paper presents and provides analysis of unsteady surface pressures measured on a model rotor blade as the blade experienced near parallel blade vortex interaction with a twin vortex system. To provide a basis for analysis, the vortex system was characterized by hot-wire measurements made in the interaction plane but in the absence of the rotor. The unsteady pressure response resulting from a single vortex interaction is then presented to provide a frame of reference for the twin vortex results. A series of twin vortex interaction cases are then presented and analyzed. It is shown that the unsteady blade pressures and forces are very sensitive to the inclination angle and separation distance of the vortex pair. When the vortex cores lie almost parallel to the blade chord, the interaction is characterized by a two-stage response associated with the sequential passage of the two cores. Conversely, when the cores lie on a plane that is almost perpendicular to the blade chord, the response is similar to that of a single vortex interaction. In all cases, the normal force response is consistent with the distribution of vertical velocity in the flow field of the vortex system. The pitching moment response, on the other hand, depends on the localized suction associated with the vortex cores as they traverse the blade chord.

Item Type:Articles
Status:Published
Refereed:Yes
Glasgow Author(s) Enlighten ID:Coton, Professor Frank
Authors: Coton, F.N., Galbraith, R.A.M., and Green, R.B.
Subjects:T Technology > TL Motor vehicles. Aeronautics. Astronautics
College/School:College of Science and Engineering > School of Engineering > Aerospace Sciences
Journal Name:Journal of Aircraft
Publisher:American Institute of Aeronautics and Astronautics
ISSN:1533-3868
Copyright Holders:Copyright © F.N. Coton
First Published:First published in Journal of Aircraft 42(6):1553-1565
Publisher Policy:Reproduced with the permission of the author

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