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Aircraft wing trailing-edge noiseThe mechanism and sound pressure level of the trailing-edge noise for two-dimensional turbulent boundary layer flow was examined. Experiment is compared with current theory. A NACA 0012 airfoil of 0.61 m chord and 0.46 m span was immersed in the laminar flow of a low turbulence open jet. A 2.54 cm width roughness strip was placed at 15 percent chord from the leading edge on both sides of the airfoil as a boundary layer trip so that two separate but statistically equivalent turbulent boundary layers were formed. Tests were performed with several trailing-edge geometries with the upstream velocity U sub infinity ranging from a value of 30.9 m/s up to 73.4 m/s. Properties of the boundary layer for the airfoil and pressure fluctuations in the vicinity of the trailing-edge were examined. A scattered pressure field due to the presence of the trailing-edge was observed and is suggested as a possible sound producing mechanism for the trailing-edge noise.
Document ID
19820003166
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Underwood, R. L. (North Carolina State Univ. Raleigh, NC, United States)
Hodgson, T. H. (North Carolina State Univ. Raleigh, NC, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-164952
Accession Number
82N11039
Funding Number(s)
CONTRACT_GRANT: NSG-1377
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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