Influence of transient flight maneuvers on rotor wake dynamics and noise radiation

Christopher C. Hennes; Hsuan Nien Chen; Kenneth S. Brentner; Shreyas Ananthan; Gordon G. Leishman

Influence of transient flight maneuvers on rotor wake dynamics and noise radiation

Christopher C. Hennes, Hsuan Nien Chen, Kenneth S. Brentner, Shreyas Ananthan, Gordon G. Leishman

Aerospace Engineering

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

22 Scopus citations

Abstract

This paper presents a study of three flight maneuvers using a rotorcraft aeroacoustics model: "pop-up," "pop-down," and an arrested descent. A time-accurate free-vortex rotor wake model and a maneuvering rotor noise prediction code were used to compute the noise. All rotorcraft motions and rigid body blade motions were included in the respective models. The wake geometry and its development is described. It is shown that the magnitude and directivity of the noise is strongly dependent on the rotor wake characteristics when blade-vortex interactions occur. In the transient arrested descent maneuver, the wake geometry becomes extremely complicated, and a significant increase in both nonimpulsive and impulsive noise is predicted.

Original language	English (US)
Pages	607-624
Number of pages	18
State	Published - 2004
Event	AHS International Decennial Specialists' Conference on Aeromechnics - San Francisco, CA, United States Duration: Jan 21 2004 → Jan 23 2004

Other

Other	AHS International Decennial Specialists' Conference on Aeromechnics
Country/Territory	United States
City	San Francisco, CA
Period	1/21/04 → 1/23/04

All Science Journal Classification (ASJC) codes

General Engineering

Cite this

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title = "Influence of transient flight maneuvers on rotor wake dynamics and noise radiation",

abstract = "This paper presents a study of three flight maneuvers using a rotorcraft aeroacoustics model: {"}pop-up,{"} {"}pop-down,{"} and an arrested descent. A time-accurate free-vortex rotor wake model and a maneuvering rotor noise prediction code were used to compute the noise. All rotorcraft motions and rigid body blade motions were included in the respective models. The wake geometry and its development is described. It is shown that the magnitude and directivity of the noise is strongly dependent on the rotor wake characteristics when blade-vortex interactions occur. In the transient arrested descent maneuver, the wake geometry becomes extremely complicated, and a significant increase in both nonimpulsive and impulsive noise is predicted.",

author = "Hennes, {Christopher C.} and Chen, {Hsuan Nien} and Brentner, {Kenneth S.} and Shreyas Ananthan and Leishman, {Gordon G.}",

year = "2004",

language = "English (US)",

pages = "607--624",

note = "AHS International Decennial Specialists' Conference on Aeromechnics ; Conference date: 21-01-2004 Through 23-01-2004",

}

TY - CONF

T1 - Influence of transient flight maneuvers on rotor wake dynamics and noise radiation

AU - Hennes, Christopher C.

AU - Chen, Hsuan Nien

AU - Brentner, Kenneth S.

AU - Ananthan, Shreyas

AU - Leishman, Gordon G.

PY - 2004

Y1 - 2004

N2 - This paper presents a study of three flight maneuvers using a rotorcraft aeroacoustics model: "pop-up," "pop-down," and an arrested descent. A time-accurate free-vortex rotor wake model and a maneuvering rotor noise prediction code were used to compute the noise. All rotorcraft motions and rigid body blade motions were included in the respective models. The wake geometry and its development is described. It is shown that the magnitude and directivity of the noise is strongly dependent on the rotor wake characteristics when blade-vortex interactions occur. In the transient arrested descent maneuver, the wake geometry becomes extremely complicated, and a significant increase in both nonimpulsive and impulsive noise is predicted.

AB - This paper presents a study of three flight maneuvers using a rotorcraft aeroacoustics model: "pop-up," "pop-down," and an arrested descent. A time-accurate free-vortex rotor wake model and a maneuvering rotor noise prediction code were used to compute the noise. All rotorcraft motions and rigid body blade motions were included in the respective models. The wake geometry and its development is described. It is shown that the magnitude and directivity of the noise is strongly dependent on the rotor wake characteristics when blade-vortex interactions occur. In the transient arrested descent maneuver, the wake geometry becomes extremely complicated, and a significant increase in both nonimpulsive and impulsive noise is predicted.

UR - http://www.scopus.com/inward/record.url?scp=2942571351&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=2942571351&partnerID=8YFLogxK

M3 - Paper

AN - SCOPUS:2942571351

SP - 607

EP - 624

T2 - AHS International Decennial Specialists' Conference on Aeromechnics

Y2 - 21 January 2004 through 23 January 2004

ER -

Influence of transient flight maneuvers on rotor wake dynamics and noise radiation

Abstract

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All Science Journal Classification (ASJC) codes

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