Active flow control technique for the reduction of helicopter BVI noise; a numerical study using large-eddy simulation

Marcel Ilie

Active flow control technique for the reduction of helicopter BVI noise; a numerical study using large-eddy simulation

Marcel Ilie

Mechanical Engineering

University of Central Florida
Materials and Aerospace Engineering

Research output: Contribution to book or proceeding › Conference article › peer-review

2 Scopus citations

Abstract

A novel technique regarding the reduction of helicopter blade-vortex interaction noise is proposed. The proposed technique is based on the idea of injecting air at the leading edge of the blade to alter the vortex characteristics (strength and core size). The numerical investigations are performed using the large-eddy simulation (LES) approach. The simulations were performed for a Reynolds number, Re = 1.3 × 10⁶, based on the NACA0012 airfoil chord and free-stream velocity. The present study shows that by injecting air at the leading edge of the blade, the influence of blade-vortex interaction on the aerodynamic coefficients and aeroacoustic noise is significantly reduced.

Original language	English
Title of host publication	16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)
State	Published - 2010
Event	16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference) - Stockholm, Sweden Duration: Jun 7 2010 → Jun 9 2010

Publication series

Name	16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)

Conference

Conference	16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)
Country/Territory	Sweden
City	Stockholm
Period	06/7/10 → 06/9/10

Scopus Subject Areas

Aerospace Engineering
Acoustics and Ultrasonics

Cite this

@inproceedings{07138f27a81346a684b5c50ebefb5c9b,

title = "Active flow control technique for the reduction of helicopter BVI noise; a numerical study using large-eddy simulation",

abstract = "A novel technique regarding the reduction of helicopter blade-vortex interaction noise is proposed. The proposed technique is based on the idea of injecting air at the leading edge of the blade to alter the vortex characteristics (strength and core size). The numerical investigations are performed using the large-eddy simulation (LES) approach. The simulations were performed for a Reynolds number, Re = 1.3 × 106, based on the NACA0012 airfoil chord and free-stream velocity. The present study shows that by injecting air at the leading edge of the blade, the influence of blade-vortex interaction on the aerodynamic coefficients and aeroacoustic noise is significantly reduced.",

author = "Marcel Ilie",

year = "2010",

language = "English",

isbn = "9781600867446",

series = "16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)",

booktitle = "16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)",

note = "16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference) ; Conference date: 07-06-2010 Through 09-06-2010",

}

Ilie, M 2010, Active flow control technique for the reduction of helicopter BVI noise; a numerical study using large-eddy simulation. in 16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)., 2010-3871, 16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference), 16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference), Stockholm, Sweden, 06/7/10.

Active flow control technique for the reduction of helicopter BVI noise; a numerical study using large-eddy simulation. / Ilie, Marcel.
16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference). 2010. 2010-3871 (16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)).

Research output: Contribution to book or proceeding › Conference article › peer-review

TY - GEN

T1 - Active flow control technique for the reduction of helicopter BVI noise; a numerical study using large-eddy simulation

AU - Ilie, Marcel

PY - 2010

Y1 - 2010

N2 - A novel technique regarding the reduction of helicopter blade-vortex interaction noise is proposed. The proposed technique is based on the idea of injecting air at the leading edge of the blade to alter the vortex characteristics (strength and core size). The numerical investigations are performed using the large-eddy simulation (LES) approach. The simulations were performed for a Reynolds number, Re = 1.3 × 106, based on the NACA0012 airfoil chord and free-stream velocity. The present study shows that by injecting air at the leading edge of the blade, the influence of blade-vortex interaction on the aerodynamic coefficients and aeroacoustic noise is significantly reduced.

AB - A novel technique regarding the reduction of helicopter blade-vortex interaction noise is proposed. The proposed technique is based on the idea of injecting air at the leading edge of the blade to alter the vortex characteristics (strength and core size). The numerical investigations are performed using the large-eddy simulation (LES) approach. The simulations were performed for a Reynolds number, Re = 1.3 × 106, based on the NACA0012 airfoil chord and free-stream velocity. The present study shows that by injecting air at the leading edge of the blade, the influence of blade-vortex interaction on the aerodynamic coefficients and aeroacoustic noise is significantly reduced.

UR - https://www.scopus.com/pages/publications/78649545931

M3 - Conference article

AN - SCOPUS:78649545931

SN - 9781600867446

T3 - 16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)

BT - 16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)

T2 - 16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference)

Y2 - 7 June 2010 through 9 June 2010

ER -

Active flow control technique for the reduction of helicopter BVI noise; a numerical study using large-eddy simulation

Abstract

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