A computational study of helicopter rotor wakes and noise generated during transient maneuvers

Hsuan Nien Chen, Kenneth Steven Brentner, Shreyas Ananthan, J. Gordon Leishman

Research output: Contribution to journalConference article

9 Citations (Scopus)

Abstract

A study of three types of flight maneuvers, namely arrested descent, turns, and roll-reversal maneuvers, were examined using a rotorcraft aeroacoustics prediction model. The components of the model comprised a utility helicopter flight dynamic model, a time-accurate free-vortex rotor wake model, and a maneuvering rotor noise prediction code. All rotorcraft motions and rigid body blade motions were included in the respective models. The rotor wake geometry and its development during the various flight maneuvers is described. In a transient maneuver, the rotor wake behavior is shown to be relatively complicated and in some cases the tip-vortices "bundle" together. The interaction of the tip vortices with the rotor blades creates a significant increase in levels of the impulsive noise, but primarily when the interaction of the nearly parallel to the blade. When a "bundle" of tip vortices interacts with the rotor in a near-parallel interaction, a very large increase in impulsive noise is observed over a very large region under the rotor.

Original languageEnglish (US)
Pages (from-to)492-517
Number of pages26
JournalAnnual Forum Proceedings - AHS International
Volume1
StatePublished - Dec 1 2005
Event61st Annual Forum Proceedings - AHS International - Grapevine, TX, United States
Duration: Jun 1 2005Jun 3 2005

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Helicopter rotors
Rotors
Vortex flow
Impulse noise
Aeroacoustics
Flight dynamics
Helicopters
Turbomachine blades
Dynamic models
Geometry

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

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abstract = "A study of three types of flight maneuvers, namely arrested descent, turns, and roll-reversal maneuvers, were examined using a rotorcraft aeroacoustics prediction model. The components of the model comprised a utility helicopter flight dynamic model, a time-accurate free-vortex rotor wake model, and a maneuvering rotor noise prediction code. All rotorcraft motions and rigid body blade motions were included in the respective models. The rotor wake geometry and its development during the various flight maneuvers is described. In a transient maneuver, the rotor wake behavior is shown to be relatively complicated and in some cases the tip-vortices {"}bundle{"} together. The interaction of the tip vortices with the rotor blades creates a significant increase in levels of the impulsive noise, but primarily when the interaction of the nearly parallel to the blade. When a {"}bundle{"} of tip vortices interacts with the rotor in a near-parallel interaction, a very large increase in impulsive noise is observed over a very large region under the rotor.",
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A computational study of helicopter rotor wakes and noise generated during transient maneuvers. / Chen, Hsuan Nien; Brentner, Kenneth Steven; Ananthan, Shreyas; Gordon Leishman, J.

In: Annual Forum Proceedings - AHS International, Vol. 1, 01.12.2005, p. 492-517.

Research output: Contribution to journalConference article

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