Numerical Simulations on the PSP Rotor Using HMB3

Jimenez-Garcia, A. and Barakos, G.N. (2018) Numerical Simulations on the PSP Rotor Using HMB3. In: AIAA Science and Technology Forum and Exposition (SciTech2018), Kissimmee, FL, USA, 8-12 Jan 2018, ISBN 9781624105241 (doi: 10.2514/6.2018-0306)

153283.pdf - Accepted Version



This work presents CFD analyses of the isolated Pressure Sensitive Paint (PSP) model rotor blade in hover and forward flight using the structured multi-block CFD solver of Glasgow University. In hover, two blade-tip Mach numbers (0.585 and 0.65) were simulated for a range of blade pitch angles using fully-turbulent flow and the k-ω SST model. Results at blade-tip Mach number of 0.585 showed a fair agreement with experimental Figure of Merit and surface pressure coefficients obtained in the Rotor Test Cell (RTC) at NASA Langley Research Center. Comparisons are presented at blade-tip Mach number of 0.65 in terms of integral blade loads, surface pressure coefficients and position of the tip-vortex cores with published numerical data. Finally, the flow around the PSP rotor in forward flight was also computed at medium thrust (CT =0.006) and results were compared with published experimental data.

Item Type:Conference Proceedings
Glasgow Author(s) Enlighten ID:Barakos, Professor George and Jimenez Garcia, Mr Antonio
Authors: Jimenez-Garcia, A., and Barakos, G.N.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Copyright Holders:Copyright © 2018 The Authors
Publisher Policy:Reproduced in accordance with the copyright policy of the publisher
Related URLs:

University Staff: Request a correction | Enlighten Editors: Update this record