Acoustic source identification for transitional airfoil flows
using cross correlations
Acoustic source identification for transitional airfoil flows
using cross correlations
Direct numerical simulations have been conducted of the flow over NACA-0006 and NACA-0012 airfoils. For all cases multiple sources of noise have been observed. At low frequencies, the contribution of trailing-edge noise radiation is significant, while for the high frequencies, the radiated noise appears to be due only to flow events in the transition/reattachment region on the suction side. Cross correlations of acoustic and hydrodynamic quantities, combined with ray-acoustic theory, are used to identify the main source locations. While the physical origin of trailing-edge noise can be clearly identified using these methods, the situation is less clear for additional noise sources that radiate at high frequency. Evidence suggests that these additional noise sources are located downstream of transition on the suction side of the airfoil, in the region directly downstream of boundary-layer reattachment.
Jones, L.E.
0a801680-fecd-400f-a771-b0ac1fcd02c6
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97
Sandberg, R.D.
41d03f60-5d12-4f2d-a40a-8ff89ef01cfa
October 2010
Jones, L.E.
0a801680-fecd-400f-a771-b0ac1fcd02c6
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97
Sandberg, R.D.
41d03f60-5d12-4f2d-a40a-8ff89ef01cfa
Jones, L.E., Sandham, N.D. and Sandberg, R.D.
(2010)
Acoustic source identification for transitional airfoil flows
using cross correlations.
AIAA Journal, 48 (10).
(doi:10.2514/1.J050345).
Abstract
Direct numerical simulations have been conducted of the flow over NACA-0006 and NACA-0012 airfoils. For all cases multiple sources of noise have been observed. At low frequencies, the contribution of trailing-edge noise radiation is significant, while for the high frequencies, the radiated noise appears to be due only to flow events in the transition/reattachment region on the suction side. Cross correlations of acoustic and hydrodynamic quantities, combined with ray-acoustic theory, are used to identify the main source locations. While the physical origin of trailing-edge noise can be clearly identified using these methods, the situation is less clear for additional noise sources that radiate at high frequency. Evidence suggests that these additional noise sources are located downstream of transition on the suction side of the airfoil, in the region directly downstream of boundary-layer reattachment.
Text
JonesSandhamSandbergAIAAJ2010.pdf
- Version of Record
Restricted to Repository staff only
Request a copy
More information
Published date: October 2010
Organisations:
Aerodynamics & Flight Mechanics
Identifiers
Local EPrints ID: 168475
URI: http://eprints.soton.ac.uk/id/eprint/168475
ISSN: 0001-1452
PURE UUID: f9065e80-7be5-4227-b4a6-232595fd3d23
Catalogue record
Date deposited: 30 Nov 2010 09:27
Last modified: 14 Mar 2024 02:42
Export record
Altmetrics
Contributors
Author:
L.E. Jones
Author:
N.D. Sandham
Author:
R.D. Sandberg
Download statistics
Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.
View more statistics