Design parameters improvement of helicopter ducted tail rotor. Issue 2 (5th March 2018)

• Record Type: Journal Article
• Authors: Zhong, Guo; Huang, Jun; Yi, Mingxu
• Is Part Of: Aircraft engineering and aerospace technology. Volume 90:Issue 2(2018)
• Page Start: 237
• Page End: 245
• Publication Date: 2018-03-05
• Subjects: Aerodynamic noise -- Computational fluid dynamics -- Ducted tail rotor -- Noise reduction; Aerospace engineering -- Periodicals; Aeronautics -- Systems engineering -- Periodicals; Astronautics -- Systems engineering -- Periodicals; Airplanes -- Equipment and supplies -- Periodicals; Space vehicles -- Equipment and supplies -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1108/AEAT-01-2017-0033
• Languages: English
• ISSNs: 1748-8842

Abstract

Abstract : Purpose: The purpose of this paper is to reduce the acoustic noise of helicopter ducted tail rotor. Design/methodology/approach: To 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. Findings: Compared with the experimental results, the proposed method of acoustic noise is rather desirable. Practical implications: Then several geometry parameters are modified to investigate the noise reduction of ducted tail rotor by using the numerical prediction method. Originality/value: The 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.