Computational investigation of blade vortex interaction noise

See Ho Wong; Michael Papadakis; Lakshmi S. Nizampatnam; Klaus A. Hoffmann; Ramesh K. Agarwal

Computational investigation of blade vortex interaction noise

See Ho Wong, Michael Papadakis, Lakshmi S. Nizampatnam, Klaus A. Hoffmann, Ramesh K. Agarwal

Research output: Contribution to conference › Paper › peer-review

Abstract

A significant source of helicopter noise is bladevortex- interaction (BVI). In a BVI, the source of the propagated wave is primarily due to the large pressure fluctuations that occur near the blade when the vortex passes immediately underneath the leading edge. This paper presents a computational methodology for predicting BVI acoustic signature. The full set of Fourier transformed linearized Euler equations were integrated to yield the acoustic signature. Computations were performed with two types of far field boundary conditions. These included standard non-reflecting boundary conditions as well as a Perfectly Matched Layer (PML) boundary. Computationarl esults obtained for a range of test configurations are presented.

Original language	English
State	Published - 2000
Event	38th Aerospace Sciences Meeting and Exhibit 2000 - Reno, NV, United States Duration: Jan 10 2000 → Jan 13 2000

Conference

Conference	38th Aerospace Sciences Meeting and Exhibit 2000
Country/Territory	United States
City	Reno, NV
Period	01/10/00 → 01/13/00

Cite this

@conference{eb7eda8422624aeb96aaf91766e8d766,

title = "Computational investigation of blade vortex interaction noise",

abstract = "A significant source of helicopter noise is bladevortex- interaction (BVI). In a BVI, the source of the propagated wave is primarily due to the large pressure fluctuations that occur near the blade when the vortex passes immediately underneath the leading edge. This paper presents a computational methodology for predicting BVI acoustic signature. The full set of Fourier transformed linearized Euler equations were integrated to yield the acoustic signature. Computations were performed with two types of far field boundary conditions. These included standard non-reflecting boundary conditions as well as a Perfectly Matched Layer (PML) boundary. Computationarl esults obtained for a range of test configurations are presented.",

author = "Wong, {See Ho} and Michael Papadakis and Nizampatnam, {Lakshmi S.} and Hoffmann, {Klaus A.} and Agarwal, {Ramesh K.}",

year = "2000",

language = "English",

note = "38th Aerospace Sciences Meeting and Exhibit 2000 ; Conference date: 10-01-2000 Through 13-01-2000",

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TY - CONF

T1 - Computational investigation of blade vortex interaction noise

AU - Wong, See Ho

AU - Papadakis, Michael

AU - Nizampatnam, Lakshmi S.

AU - Hoffmann, Klaus A.

AU - Agarwal, Ramesh K.

PY - 2000

Y1 - 2000

N2 - A significant source of helicopter noise is bladevortex- interaction (BVI). In a BVI, the source of the propagated wave is primarily due to the large pressure fluctuations that occur near the blade when the vortex passes immediately underneath the leading edge. This paper presents a computational methodology for predicting BVI acoustic signature. The full set of Fourier transformed linearized Euler equations were integrated to yield the acoustic signature. Computations were performed with two types of far field boundary conditions. These included standard non-reflecting boundary conditions as well as a Perfectly Matched Layer (PML) boundary. Computationarl esults obtained for a range of test configurations are presented.

AB - A significant source of helicopter noise is bladevortex- interaction (BVI). In a BVI, the source of the propagated wave is primarily due to the large pressure fluctuations that occur near the blade when the vortex passes immediately underneath the leading edge. This paper presents a computational methodology for predicting BVI acoustic signature. The full set of Fourier transformed linearized Euler equations were integrated to yield the acoustic signature. Computations were performed with two types of far field boundary conditions. These included standard non-reflecting boundary conditions as well as a Perfectly Matched Layer (PML) boundary. Computationarl esults obtained for a range of test configurations are presented.

UR - http://www.scopus.com/inward/record.url?scp=84894382309&partnerID=8YFLogxK

M3 - Paper

AN - SCOPUS:84894382309

T2 - 38th Aerospace Sciences Meeting and Exhibit 2000

Y2 - 10 January 2000 through 13 January 2000

ER -

Computational investigation of blade vortex interaction noise

Abstract

Conference

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