Tiltrotor CFD part I: validation

Jimenez Garcia, A., Barakos, G. N. and Gates, S. (2017) Tiltrotor CFD part I: validation. Aeronautical Journal, 121(1239), pp. 577-610. (doi: 10.1017/aer.2017.17)

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This paper presents performance analyses of the model-scale ERICA and TILTAERO tiltrotors and of the full-scale XV-15 rotor with high-fidelity computational fluids dynamics. For the ERICA tiltrotor, the overall effect of the blades on the fuselage was well captured, as demonstrated by analysing surface pressure measurements. However, there was no available experimental data for the blade aerodynamic loads. A comparison of computed rotor loads with experiments was instead possible for the XV-15 rotor, where CFD results predicted the FoM within 1.05%. The method was also able to capture the differences in performance between hover and propeller modes. Good agreement was also found for the TILTAERO loads. The overall agreement with the experimental data and theory for the considered cases demonstrates the capability of the present CFD method to accurately predict tiltrotor flows. In a second part of this work, the validated method is used for blade shape optimisation.

Item Type:Articles
Additional Information:The use of the cluster Chadwick of the University of Liverpool is gratefully acknowledged. Some results were obtained using the EPSRC funded ARCHIE-WeSt High Performance Computer (www.archie-west.ac.uk), EPSRC grant no. EP/K000586/1. Part of this work is funded under the HiperTilt Project of the UK Technology Strategy Board (TSB) and Leonardo Helicopters under Contract Nr. 101370.
Glasgow Author(s) Enlighten ID:Barakos, Professor George and Jimenez Garcia, Mr Antonio
Authors: Jimenez Garcia, A., Barakos, G. N., and Gates, S.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Journal Name:Aeronautical Journal
Publisher:Royal Aeronautical Society
ISSN (Online):2059-6464
Published Online:05 May 2017
Copyright Holders:Copyright © 2017 Royal Aeronautical Society
First Published:First published in Aeronautical Journal 121(1239): 577-610
Publisher Policy:Reproduced in accordance with the copyright policy of the publisher

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