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An Aeroacoustic Study of a Leading Edge Slat ConfigurationAeroacoustic evaluations of high-lift devices have been carried out in the Quiet Flow Facility of the NASA Langley Research Center. The present paper describes detailed flow and acoustic measurements that have been made in order to better understand the noise generated from airflow over a wing leading edge slat configuration, and to possibly predict and reduce this noise source. The acoustic database is obtained by a moveable Small Aperture Directional Array of microphones designed to electronically steer to different portions of models under study. The slat is shown to be a uniform distributed noise source. The data was processed such that spectra and directivity were determined with respect to a one-foot span of slat. The spectra are normalized in various fashions to demonstrate slat noise character. In order to equate portions of the spectra to different slat noise components, trailing edge noise predictions using measured slat boundary layer parameters as inputs are compared to the measured slat noise spectra.
Document ID
20030032411
Acquisition Source
Langley Research Center
Document Type
Reprint (Version printed in journal)
External Source(s)
doi:10.1260/147547202320962583
Authors
Mendoza, J. M. (Honeywell Engines, Systems and Services Phoenix, AZ, United States)
Brooks, T. F. (NASA Langley Research Center Hampton, VA, United States)
Humphreys, W. M., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 8, 2013
Publication Date
January 1, 2002
Publication Information
Publication: Aeroacoustics
Publisher: Multi-Science Publishing Co. Ltd.
Volume: 1
Issue: 3
Subject Category
Acoustics
Distribution Limits
Public
Copyright
Public Use Permitted.

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