Design parameters improvement of helicopter ducted tail rotor

Design parameters improvement of helicopter ducted tail rotor PurposeThe purpose of this paper is to reduce the acoustic noise of helicopter ducted tail rotor.Design/methodology/approachTo predict the noise accurately, a thin-body boundary element method (BEM)/Ffowcs Williams–Hawkings method is developed in this paper. It is a hybrid method combining the BEM with computational aeroacoustics and can be used efficiently to predict the propagation of sound wave in the duct.FindingsCompared with the experimental results, the proposed method of acoustic noise is rather desirable.Practical implicationsThen several geometry parameters are modified to investigate the noise reduction of ducted tail rotor by using the numerical prediction method.Originality/valueThe aerodynamic and acoustic performance of different modification tasks is discussed. These results demonstrate the validity of design parameters modification of ducted tail rotor in acoustic noise reduction. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Design parameters improvement of helicopter ducted tail rotor

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Publisher
Emerald Group Publishing Limited
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
1748-8842
D.O.I.
10.1108/AEAT-01-2017-0033
Publisher site
See Article on Publisher Site

Abstract

PurposeThe purpose of this paper is to reduce the acoustic noise of helicopter ducted tail rotor.Design/methodology/approachTo predict the noise accurately, a thin-body boundary element method (BEM)/Ffowcs Williams–Hawkings method is developed in this paper. It is a hybrid method combining the BEM with computational aeroacoustics and can be used efficiently to predict the propagation of sound wave in the duct.FindingsCompared with the experimental results, the proposed method of acoustic noise is rather desirable.Practical implicationsThen several geometry parameters are modified to investigate the noise reduction of ducted tail rotor by using the numerical prediction method.Originality/valueThe aerodynamic and acoustic performance of different modification tasks is discussed. These results demonstrate the validity of design parameters modification of ducted tail rotor in acoustic noise reduction.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Mar 5, 2018

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