Numerical Simulation of Aeroacoustics of Hovering Helicopter Rotor

A N Kusyumov,K V Fayzullin,S A Mikhailov,G N Barakos,S A Kusyumov

doi:10.1088/1757-899x/449/1/012017

Abstract

The specifics of the problem of estimating the noise of a hovering rotor, allows for some simplification of the Ffowcs Williams-Hawkins (FW-H) equation. Most published works dedicated to helicopter tonal noise estimates use the far-field formulation. This paper estimates the aeroacoustic emissions of a helicopter rotor in hover, for observers placed at different distances using the FW-H equation, including near-field and far-field terms. The blade pressure distribution is obtained from numerical simulations with the RANS equations. To demonstrate this approach, the near- and far-field contributions are analyzed for the model-scale UH-1H main helicopter rotor. For the numerical simulations, the HMB solver of Glasgow University and the ANSYS Fluent13 commercial solver are used. As the rotor blade behaviour is characterized by a complex motion in the computer program it is assumed that the blade is seen in as a rotating rigid body. The most commonly used mathematical model of the FW-H equation corresponds to the classical impermeable formulation. In this case, the source surface corresponds to the blade surface. Then, the acoustic pressure (based on the FW-H 1A formulation) is modified with empirical adjustments, based on the radiation Mach number. This was applied for the near- or far-field thickness noise depending on the rotor-observer distance.

Highlights

The prediction of aircraft noise falls in the area of Computational Aeroacoustics (CAA)
CAA combines flow data obtained by Computational Fluid Dynamics (CFD) for a region near the aircraft surface, and wave propagation equations, to estimate the aircraft noise far away from their sources
Application of the in-house code for the FW–H (Ffowcs Williams – Hawkings) numerical solution was considered for near-field observers

Summary

Introduction

The prediction of aircraft noise falls in the area of Computational Aeroacoustics (CAA). CAA combines flow data obtained by Computational Fluid Dynamics (CFD) for a region near the aircraft surface, and wave propagation equations, to estimate the aircraft noise far away from their sources. There are two main components contributing to the generation of near- and far-field noise, the main rotor and the tail rotor [1]. The helicopter main rotor generates tonal and broadband noise. Most of works on helicopter rotor noise employ the Ffowcs Williams-Hawkings (FW-H) equation [2]. This equation separates the noise in thickness and loading noise components, and its general formulation allows for estimates of the acoustic emissions for observers in the near- and farfield of the rotor.

Published under licence by IOP Publishing Ltd

Conclusions