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The Effect of a Boundary Layer on Engine Noise propagating to the Fuselage at Flight Conditions

Dierke, Jürgen and Ewert, Roland and Delfs, Jan and Stöhr, Christian and Rose, Marco (2013) The Effect of a Boundary Layer on Engine Noise propagating to the Fuselage at Flight Conditions. In: 19th AIAA/CEAS Aeroacoustics Conference. 19th AIAA/CEAS Aeroacoustics Conference, 27.-29. Mai 2013, Berlin, Deutschland. doi: 10.2514/6.2013-2006.

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Engine noise transmitted through the fuselage causes a significant part of the cabin noise. In a previous work a Computational Aeroacoustics (CAA) technique was introduced that takes into account the effect of non-stationary fluctuating boundary layer on sound propagation. It showed a considerable change of the sound field reaching the fuselage due to refraction in the boundary layer. The sound propagation is calculated solving the linearised Euler equations over a viscous Reynolds-averaged Navier-Stokes (RANS) flow. Turbulent scattering is considered by augmenting the steady flow computation with turbulent fluctuations reconstructed stochastically using the Random-Particle-Method (RPM) based on RANS turbulence statistics. In this study realistic engine fan modes at 2850 Hz are used as a sound source together with a free flow Mach number of 0.85. The noise emission from the engine intake exhibits a distinct directivity with highly increased sound radiation in direction normal to the axis of rotation of the fan. However the refraction shows a strong influence on the sound pressure level. The effect of the scattering is more subtle including the build-up of spectral haystacks (broadband humps next to the tone frequency) as well as a frequency shift of the spectral maximum towards higher frequencies. Especially the frequency shift can be very important for the assessment of the structural response of the fuselage skin to the acoustic surface pressure.

Item URL in elib:https://elib.dlr.de/84086/
Document Type:Conference or Workshop Item (Speech)
Title:The Effect of a Boundary Layer on Engine Noise propagating to the Fuselage at Flight Conditions
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Date:27 May 2013
Journal or Publication Title:19th AIAA/CEAS Aeroacoustics Conference
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:Aeroakustik, Aeroacoustics, TBL, turbulent boundary layer, CAA, RPM, stochastic
Event Title:19th AIAA/CEAS Aeroacoustics Conference
Event Location:Berlin, Deutschland
Event Type:international Conference
Event Dates:27.-29. Mai 2013
Organizer: AIAA/CEAS
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Simulation & Validation (old)
Location: Braunschweig
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Technical Acoustics
Deposited By: Dierke, Jürgen
Deposited On:09 Sep 2013 13:46
Last Modified:19 Jul 2023 14:57

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