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)
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117084.pdf - Accepted Version 7MB |
Abstract
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). |
| Status: | Published |
| Refereed: | Yes |
| 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: | 0001-9240 |
| 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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