This paper describes a new method for computing the flowfield and acoustic signature of arbitrary rotor in forward flight. The overall scheme solves the Navier-Stokes equations on a system of overset grids. These grids allow for prescribed cyclic and flapping blade motions and capture the interactions between the rotor blades and wake. The far-field noise is computed with an acoustic integral over a surface that completely encloses the rotor blades. Interpolations onto this acoustic surface use the same overset-grid techniques that are used for the flowfield solution. As a demonstration of the overall prediction scheme, computed and experimental far-field noise results are compared in cases with high-speed impulsive (HSI) and blade-vortex interaction (BVI) noise. Computed HSI noise shows excellent agreement with experimental data in the plane of the rotor. Out-of-plane HSI and BVI predictions require improved grid resolution in the rotor wake to capture the details of the high-frequency loading noise.
Rotorcraft aeroacoustics computations with overset-grid CFD methods
Aeroakustische Rotorberechnungen mit 'Overset-Netz'-CFD-Methoden
Journal of the American Helicopter Society ; 44 , 2 ; 132-140
1999
9 Seiten, 8 Bilder, 3 Tabellen, 20 Quellen
Article (Journal)
English
Rotorcraft Aeroacoustics Computations with Overset-Grid CFD Methods
Online Contents | 1999
|Provably stable overset grid methods for computational aeroacoustics
Online Contents | 2011
|Unstructured Overset Grid Adaptation for Rotorcraft Aerodynamic Interactions
British Library Conference Proceedings | 2011
|NTIS | 1990
|Computations of Rotorcraft Aeroacoustics with a Navier-Stokes/Kirchhoff Method
British Library Conference Proceedings | 1996
|