Validation of the steady state hover formulation for accurate performance predictions

Fitzgibbon, T.A., Woodgate, M.A., Jimenez-Garcia, A. and Barakos, G.N. (2019) Validation of the steady state hover formulation for accurate performance predictions. AIAA Journal, 57(12), pp. 5293-5308. (doi: 10.2514/1.J058408)

Abstract

This paper shows accurate predictions for hover performance regardless of planform geometry, blade-tip Mach number, or disk loading. To prove this statement, sensitivity analyses were performed along with performance predictions for four rotor designs. Planform effects were also studied, such as the blade anhedral, showing the strong sensitivity of the rotor blade performance due to geometric features. The steady-state solution methodology with imposed Froude boundary conditions is shown to give accurate results for relatively coarse grid sizes. This approach leads to reduced computational costs as compared to time-dependent simulations. It is also recognized that, given the current accuracy of the available experimental data, the use of more advanced computational fluid dynamics methods may not be fully justified. To advance the accuracy of modern computational fluid dynamics methods, a comprehensive experimental dataset is required.

• Item Type: Articles
• Additional Information: This work is funded by DSTL (Defence Science and Technology Laboratory), Contract No. 74260. A part of the technical work has been completed under the collaboration project, TTCP AER CP13.A1, Next Generation Rotor Blade Design. Results were obtained using the EPSRC funded ARCHIE-WeSt High Performance Computer (www.archiewest. ac.uk). EPSRC grant no. EP/K000586/1.
• Status: Published
• Refereed: Yes
• Glasgow Author(s) Enlighten ID: Barakos, Professor George and Woodgate, Dr Mark and Fitzgibbon, Thomas and Jimenez Garcia, Mr Antonio
• Authors: Fitzgibbon, T.A., Woodgate, M.A., Jimenez-Garcia, A., and Barakos, G.N.
• College/School: College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
• Journal Name: AIAA Journal
• Publisher: American Institute of Aeronautics and Astronautics, Inc.
• ISSN: 0001-1452
• ISSN (Online): 1533-385X
• Published Online: 28 August 2019
• Copyright Holders: Copyright © 2019 The Authors
• First Published: First published in AIAA Journal 57(12):5293-5308
• Publisher Policy: Reproduced in accordance with the copyright policy of the publisher