High angle of attack helicopter blade-vortex interaction; numerical studies using LES

Husam Al-Kuran; Patricia Coronado; Marcel Ilie; Ge Cheng Zha

High angle of attack helicopter blade-vortex interaction; numerical studies using LES

Husam Al-Kuran, Patricia Coronado, Marcel Ilie, Ge Cheng Zha

Mechanical Engineering

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

Abstract

The influence of angle of attack on the helicopter blade-vortex mechanism of interaction is investigated using large eddy simulation (LES). The LES technique provides a promising tool for obtaining the unsteady wall-pressure fields, aerodynamic coefficients and the acoustic source functions. A large eddy simulation is carried out for a two-dimensional Blade-Vortex Interaction (BVI) problem, for a chord based Reynolds number of 1.3x106. Computations are carried out to investigate the influence of angle of attack (α = 0^θ, α = 5^θ, α = 10^θ) on the aerodynamic coefficients and acoustic field.

Original language	English
Title of host publication	20th AIAA Computational Fluid Dynamics Conference 2011
State	Published - 2011
Event	20th AIAA Computational Fluid Dynamics Conference 2011 - Honolulu, HI, United States Duration: Jun 27 2011 → Jun 30 2011

Publication series

Name	20th AIAA Computational Fluid Dynamics Conference 2011

Conference

Conference	20th AIAA Computational Fluid Dynamics Conference 2011
Country/Territory	United States
City	Honolulu, HI
Period	06/27/11 → 06/30/11

Scopus Subject Areas

Fluid Flow and Transfer Processes
Energy Engineering and Power Technology
Aerospace Engineering
Mechanical Engineering

Cite this

@inproceedings{88e385ac4a1a420abcc99a9db389f9a8,

title = "High angle of attack helicopter blade-vortex interaction; numerical studies using LES",

abstract = "The influence of angle of attack on the helicopter blade-vortex mechanism of interaction is investigated using large eddy simulation (LES). The LES technique provides a promising tool for obtaining the unsteady wall-pressure fields, aerodynamic coefficients and the acoustic source functions. A large eddy simulation is carried out for a two-dimensional Blade-Vortex Interaction (BVI) problem, for a chord based Reynolds number of 1.3x106. Computations are carried out to investigate the influence of angle of attack (α = 0θ, α = 5θ, α = 10θ) on the aerodynamic coefficients and acoustic field.",

author = "Husam Al-Kuran and Patricia Coronado and Marcel Ilie and Zha, {Ge Cheng}",

year = "2011",

language = "English",

isbn = "9781624101489",

series = "20th AIAA Computational Fluid Dynamics Conference 2011",

booktitle = "20th AIAA Computational Fluid Dynamics Conference 2011",

note = "20th AIAA Computational Fluid Dynamics Conference 2011 ; Conference date: 27-06-2011 Through 30-06-2011",

}

TY - GEN

T1 - High angle of attack helicopter blade-vortex interaction; numerical studies using LES

AU - Al-Kuran, Husam

AU - Coronado, Patricia

AU - Ilie, Marcel

AU - Zha, Ge Cheng

PY - 2011

Y1 - 2011

N2 - The influence of angle of attack on the helicopter blade-vortex mechanism of interaction is investigated using large eddy simulation (LES). The LES technique provides a promising tool for obtaining the unsteady wall-pressure fields, aerodynamic coefficients and the acoustic source functions. A large eddy simulation is carried out for a two-dimensional Blade-Vortex Interaction (BVI) problem, for a chord based Reynolds number of 1.3x106. Computations are carried out to investigate the influence of angle of attack (α = 0θ, α = 5θ, α = 10θ) on the aerodynamic coefficients and acoustic field.

AB - The influence of angle of attack on the helicopter blade-vortex mechanism of interaction is investigated using large eddy simulation (LES). The LES technique provides a promising tool for obtaining the unsteady wall-pressure fields, aerodynamic coefficients and the acoustic source functions. A large eddy simulation is carried out for a two-dimensional Blade-Vortex Interaction (BVI) problem, for a chord based Reynolds number of 1.3x106. Computations are carried out to investigate the influence of angle of attack (α = 0θ, α = 5θ, α = 10θ) on the aerodynamic coefficients and acoustic field.

UR - http://www.scopus.com/inward/record.url?scp=84880641769&partnerID=8YFLogxK

M3 - Conference article

AN - SCOPUS:84880641769

SN - 9781624101489

T3 - 20th AIAA Computational Fluid Dynamics Conference 2011

BT - 20th AIAA Computational Fluid Dynamics Conference 2011

T2 - 20th AIAA Computational Fluid Dynamics Conference 2011

Y2 - 27 June 2011 through 30 June 2011

ER -

High angle of attack helicopter blade-vortex interaction; numerical studies using LES

Abstract

Publication series

Conference

Scopus Subject Areas

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