High-fidelity numerical analysis and optimisation of ducted propeller aerodynamics and acoustics

Zhang, T. and Barakos, G. (2021) High-fidelity numerical analysis and optimisation of ducted propeller aerodynamics and acoustics. Aerospace Science and Technology, 113, 106708. (doi: 10.1016/j.ast.2021.106708)

Abstract

This paper presents numerical analyses of aerodynamics and aeroacoustics of ducted/un-ducted propellers based on high-fidelity CFD methods, and adjoint-based aerodynamic performance optimisation of the ducted propeller by altering the duct and blade shapes. Ducted propeller experiments by NASA are chosen for validation and used as baseline designs. High-fidelity CFD simulations are performed using the in-house solver HMB3. The aeroacoustics is analysed using the CFD solutions and in-house codes based on FW-H equations. The aerodynamic and near-/far-field acoustic benefits by ducting are shown quantitatively. An adjoint-based aerodynamic optimisation framework is also applied to the ducted propeller by altering the duct shape and the blade twist distribution. The optimisation shows improved performance for the ducted propeller over the initial design, especially at higher blade pitch. The far-field acoustic benefits of the optimised designs are also examined and are maintained after the optimisation.

• Item Type: Articles
• Additional Information: The sponsorship of the University of Glasgow and the China Scholarship Council is gratefully acknowledged.
• Status: Published
• Refereed: Yes
• Glasgow Author(s) Enlighten ID: Barakos, Professor George and Zhang, Mr Tao
• Authors: Zhang, T., and Barakos, G.
• College/School: College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
• Journal Name: Aerospace Science and Technology
• Publisher: Elsevier
• ISSN: 1270-9638
• ISSN (Online): 1626-3219
• Published Online: 06 April 2021
• Copyright Holders: Copyright © 2021 Elsevier Masson SAS
• First Published: First published in Aerospace Science and Technology 113: 106708
• Publisher Policy: Reproduced in accordance with the publisher copyright policy