Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element Method
A detailed aerodynamic performance of a ducted tail rotor in hover has been numerically studied using CFD technique. The general governing equations of turbulent flow around ducted tail rotor are given and directly solved by using finite volume discretization and Runge-Kutta time integration. The ca...
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Series: | Mathematical Problems in Engineering |
Online Access: | http://dx.doi.org/10.1155/2017/5726253 |
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doaj-5f64e31b73e241d8a560fe3d73df279f2020-11-24T23:45:10ZengHindawi LimitedMathematical Problems in Engineering1024-123X1563-51472017-01-01201710.1155/2017/57262535726253Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element MethodYunpeng Ma0Mingxu Yi1Lifeng Wang2Jun Huang3School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaA detailed aerodynamic performance of a ducted tail rotor in hover has been numerically studied using CFD technique. The general governing equations of turbulent flow around ducted tail rotor are given and directly solved by using finite volume discretization and Runge-Kutta time integration. The calculations of the lift characteristics of the ducted tail rotor can be obtained. In order to predict the aerodynamic noise, a hybrid method combining computational aeroacoustic with boundary element method (BEM) has been proposed. The computational steps include the following: firstly, the unsteady flow around rotor is calculated using the CFD method to get the noise source information; secondly, the radiate sound pressure is calculated using the acoustic analogy Curle equation in the frequency domain; lastly, the scattering effect of the duct wall on the propagation of the sound wave is presented using an acoustic thin-body BEM. The aerodynamic results and the calculated sound pressure levels are compared with the known technique for validation. The sound pressure directivity and scattering effect are shown to demonstrate the validity and applicability of the method.http://dx.doi.org/10.1155/2017/5726253 |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Yunpeng Ma Mingxu Yi Lifeng Wang Jun Huang |
spellingShingle |
Yunpeng Ma Mingxu Yi Lifeng Wang Jun Huang Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element Method Mathematical Problems in Engineering |
author_facet |
Yunpeng Ma Mingxu Yi Lifeng Wang Jun Huang |
author_sort |
Yunpeng Ma |
title |
Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element Method |
title_short |
Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element Method |
title_full |
Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element Method |
title_fullStr |
Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element Method |
title_full_unstemmed |
Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element Method |
title_sort |
computation of aerodynamic noise radiated from ducted tail rotor using boundary element method |
publisher |
Hindawi Limited |
series |
Mathematical Problems in Engineering |
issn |
1024-123X 1563-5147 |
publishDate |
2017-01-01 |
description |
A detailed aerodynamic performance of a ducted tail rotor in hover has been numerically studied using CFD technique. The general governing equations of turbulent flow around ducted tail rotor are given and directly solved by using finite volume discretization and Runge-Kutta time integration. The calculations of the lift characteristics of the ducted tail rotor can be obtained. In order to predict the aerodynamic noise, a hybrid method combining computational aeroacoustic with boundary element method (BEM) has been proposed. The computational steps include the following: firstly, the unsteady flow around rotor is calculated using the CFD method to get the noise source information; secondly, the radiate sound pressure is calculated using the acoustic analogy Curle equation in the frequency domain; lastly, the scattering effect of the duct wall on the propagation of the sound wave is presented using an acoustic thin-body BEM. The aerodynamic results and the calculated sound pressure levels are compared with the known technique for validation. The sound pressure directivity and scattering effect are shown to demonstrate the validity and applicability of the method. |
url |
http://dx.doi.org/10.1155/2017/5726253 |
work_keys_str_mv |
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1725497050845413376 |