A novel concept towards the reduction of helicopter blade-vortex interaction; a numerical study using large-eddy simulation

Marcel Ilie

A novel concept towards the reduction of helicopter blade-vortex interaction; a numerical study using large-eddy simulation

Marcel Ilie

Mechanical Engineering

University of California, San Diego

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

Abstract

A novel technique regarding the reduction of the influence of helicopter blade-vortex interaction on the aerodynamic coefficients is proposed. The proposed technique is based on the idea of injecting air at the leading edge of the blade to alter the characteristics of the vortex. The numerical investigations are performed using the large-eddy simulation (LES) approach. The simulations were performed for a Reynolds number, Re = 1.3 × 10 ⁶, based on the NACA0012 airfoil chord and free-stream velocity. The present study shows that using the leading edge air mass injection (LEAMI) concept, the influence of blade-vortex interaction on the aerodynamic coefficients is significantly reduced.

Original language	English
Title of host publication	19th AIAA Computational Fluid Dynamics Conference
State	Published - 2009
Event	19th AIAA Computational Fluid Dynamics Conference - San Antonio, TX, United States Duration: Jun 22 2009 → Jun 25 2009

Publication series

Name	19th AIAA Computational Fluid Dynamics Conference

Conference

Conference	19th AIAA Computational Fluid Dynamics Conference
Country/Territory	United States
City	San Antonio, TX
Period	06/22/09 → 06/25/09

Scopus Subject Areas

Engineering (miscellaneous)
Automotive Engineering

Cite this

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title = "A novel concept towards the reduction of helicopter blade-vortex interaction; a numerical study using large-eddy simulation",

abstract = "A novel technique regarding the reduction of the influence of helicopter blade-vortex interaction on the aerodynamic coefficients is proposed. The proposed technique is based on the idea of injecting air at the leading edge of the blade to alter the characteristics of the vortex. The numerical investigations are performed using the large-eddy simulation (LES) approach. The simulations were performed for a Reynolds number, Re = 1.3 × 10 6, based on the NACA0012 airfoil chord and free-stream velocity. The present study shows that using the leading edge air mass injection (LEAMI) concept, the influence of blade-vortex interaction on the aerodynamic coefficients is significantly reduced.",

author = "Marcel Ilie",

year = "2009",

language = "English",

isbn = "9781563479755",

series = "19th AIAA Computational Fluid Dynamics Conference",

booktitle = "19th AIAA Computational Fluid Dynamics Conference",

note = "19th AIAA Computational Fluid Dynamics Conference ; Conference date: 22-06-2009 Through 25-06-2009",

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T1 - A novel concept towards the reduction of helicopter blade-vortex interaction; a numerical study using large-eddy simulation

AU - Ilie, Marcel

PY - 2009

Y1 - 2009

N2 - A novel technique regarding the reduction of the influence of helicopter blade-vortex interaction on the aerodynamic coefficients is proposed. The proposed technique is based on the idea of injecting air at the leading edge of the blade to alter the characteristics of the vortex. The numerical investigations are performed using the large-eddy simulation (LES) approach. The simulations were performed for a Reynolds number, Re = 1.3 × 10 6, based on the NACA0012 airfoil chord and free-stream velocity. The present study shows that using the leading edge air mass injection (LEAMI) concept, the influence of blade-vortex interaction on the aerodynamic coefficients is significantly reduced.

AB - A novel technique regarding the reduction of the influence of helicopter blade-vortex interaction on the aerodynamic coefficients is proposed. The proposed technique is based on the idea of injecting air at the leading edge of the blade to alter the characteristics of the vortex. The numerical investigations are performed using the large-eddy simulation (LES) approach. The simulations were performed for a Reynolds number, Re = 1.3 × 10 6, based on the NACA0012 airfoil chord and free-stream velocity. The present study shows that using the leading edge air mass injection (LEAMI) concept, the influence of blade-vortex interaction on the aerodynamic coefficients is significantly reduced.

UR - https://www.scopus.com/pages/publications/77958497259

M3 - Conference article

AN - SCOPUS:77958497259

SN - 9781563479755

T3 - 19th AIAA Computational Fluid Dynamics Conference

BT - 19th AIAA Computational Fluid Dynamics Conference

T2 - 19th AIAA Computational Fluid Dynamics Conference

Y2 - 22 June 2009 through 25 June 2009

ER -

A novel concept towards the reduction of helicopter blade-vortex interaction; a numerical study using large-eddy simulation

Abstract

Publication series

Conference

Scopus Subject Areas

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