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Investigation of Rotor Noise Shielding Effects by the Helicopter Fuselage in Forward Flight

Yin, Jianping (2019) Investigation of Rotor Noise Shielding Effects by the Helicopter Fuselage in Forward Flight. Journal of Aircraft, 56 (4), pp. 1-12. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.C035009. ISSN 0021-8669.

Full text not available from this repository.

Abstract

This paper presents a numerical study on the rotor noise shielding effects by the helicopter fuselage. The method used to assess acoustic shielding is based on a fast multipole boundary element method, which includes the Forward flight effect. A free-wake unsteady panel method, in combination with a Ffowcs Williams–Hawkings (FW-H) integral formulation, is used to compute the rotor noise sources for the blade vortex interaction flight condition. The prediction methodologies are described. Validation of boundary element method and the forward flight effect by means of Taylor’s transformation are conducted by using analytic solutions. The error estimation for the case without mean flow indicates that for sufficient grid resolution the maximum error occurring in the shadow region is less than 0.06 dB. The error estimation for the Taylor Transformation shows that the error can be up to 6% for M=0.2. In addition, a Kirchhoff source surface model used to treat the real rotor noise is described. Finally, the method is applied to a BO105 wind tunnel model to understand the noise shielding features of the main and tail Rotors.

Item URL in elib:https://elib.dlr.de/128674/
Document Type:Article
Title:Investigation of Rotor Noise Shielding Effects by the Helicopter Fuselage in Forward Flight
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Yin, JianpingJianping.Yin (at) dlr.deUNSPECIFIED
Date:July 2019
Journal or Publication Title:Journal of Aircraft
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:56
DOI :10.2514/1.C035009
Page Range:pp. 1-12
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
ISSN:0021-8669
Status:Published
Keywords:Helicopter Acoustics, Rotorcraft Fuselage Scattering, Computational Aeroacoustic, Installation Effects, noise Propagation, Boundary Element Method, free-wake unsteady panel method, Ffowcs Williams–Hawkings (FW-H)
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:rotorcraft
DLR - Research area:Aeronautics
DLR - Program:L RR - Rotorcraft Research
DLR - Research theme (Project):L - The Quiet und Comfortable Rotorcraft (old)
Location: Braunschweig
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Helicopter, BS
Deposited By: Yin, Dr.-Ing. Jianping
Deposited On:23 Oct 2019 13:54
Last Modified:23 Oct 2019 13:54

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