Author:
Zhong Guo,Huang Jun,Yi Mingxu
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.
Reference28 articles.
1. Numerical prediction of tonal noise generation in an inlet vaned low-speed axial fan using a hybrid aeroacoustic approach;Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science,2009
2. Analytical comparison of the acoustic analogy and Kirchhoff formulation for moving surfaces;AIAA Journal,1998
3. The sound field of a rotor in a stationary duct;Journal of Sound and Vibration,2003
4. Axial flow fan broad-band noise and prediction;Journal of Sound and Vibration,2007
5. Helicopter rotor shape optimization for the improvement of aeroacoustic performance in hover;Journal of Aircraft,2010