CFD analysis of hover performance of rotors at full and model-scale conditions

Jimenez Garcia, A. and Barakos, G. N. (2016) CFD analysis of hover performance of rotors at full and model-scale conditions. Aeronautical Journal, 120(1231), pp. 1386-1424. (doi: 10.1017/aer.2016.58)

117084.pdf - Accepted Version



Analysis of the performance of a 1/4.71 model-scale and full-scale Sikorsky S-76 main rotor in hover is presented using the multi-block CFD solver of Glasgow University. For the model-scale blade, three different tip shapes were compared for a range of collective pitch and tip Mach numbers. It was found that the anhedral tip provided the highest Figure of Merit. Rigid and elastic full-scale S-76 rotor blades were investigated using a loosely coupled CFD/CSD method. Results showed that aeroelastic effects were more significant for high thrust cases. Finally, an acoustic study was performed in the tip- path-plane of both rotors, showing good agreement in the thickness and loading noise with the theory. For the anhedral tip of the model-scale blade, a reduction of 5% of the noise level was predicted. The overall good agreement with the theory and experimental data demonstrated the capability of the present CFD method to predict rotor flows accurately.

Item Type:Articles
Additional Information:Part of this work is funded under the HiperTilt Project of the UK Technology Strategy Board (TSB) and AugustaWestland (AW).
Glasgow Author(s) Enlighten ID:Barakos, Professor George
Authors: Jimenez Garcia, A., and Barakos, G. N.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Journal Name:Aeronautical Journal
Publisher:Cambridge University Press
ISSN (Online):2059-6464
Published Online:13 June 2016
Copyright Holders:Copyright © 2016 Royal Aeronautical Society
First Published:First published in Aeronautical Journal 120(1231): 1386-1424
Publisher Policy:Reproduced in accordance with the copyright policy of the publisher.

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