Reduction of Helicopter BVI Noise Using Active Flow Control: The Case of Vortex Street Interactions

Carlos Velez; Marcel Ilie

doi:10.2514/6.2012-3031

Reduction of Helicopter BVI Noise Using Active Flow Control: The Case of Vortex Street Interactions

Carlos Velez, Marcel Ilie

Mechanical Engineering

University of Central Florida

Research output: Contribution to book or proceeding › Chapter

1 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 x 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	American English
Title of host publication	Proceedings of the Applied Aerodynamics Conference
DOIs	https://doi.org/10.2514/6.2012-3031
State	Published - Jun 25 2012

Keywords

Active flow
BVI noise
Flow control
Helicopter
Helicopter BVI
Vortex street interactions

DC Disciplines

Mechanical Engineering

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10.2514/6.2012-3031License: Unspecified

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title = "Reduction of Helicopter BVI Noise Using Active Flow Control: The Case of Vortex Street Interactions",

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 x 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.",

keywords = "Active flow, BVI noise, Flow control, Helicopter, Helicopter BVI, Vortex street interactions",

author = "Carlos Velez and Marcel Ilie",

year = "2012",

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doi = "10.2514/6.2012-3031",

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AU - Velez, Carlos

AU - Ilie, Marcel

PY - 2012/6/25

Y1 - 2012/6/25

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 x 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 x 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.

KW - Active flow

KW - BVI noise

KW - Flow control

KW - Helicopter

KW - Helicopter BVI

KW - Vortex street interactions

UR - https://doi.org/10.2514/6.2012-3031

U2 - 10.2514/6.2012-3031

DO - 10.2514/6.2012-3031

M3 - Chapter

BT - Proceedings of the Applied Aerodynamics Conference

ER -

Reduction of Helicopter BVI Noise Using Active Flow Control: The Case of Vortex Street Interactions

Abstract

Keywords

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