Title

Active Flow Control Technique For The Reduction Of Helicopter Bvi Noise; A Numerical Study Using Les

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. Copyright © 2010 by Marcel Ilie.

Publication Date

12-13-2010

Publication Title

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

Socpus ID

78649867629 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/78649867629

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