Abstract
An extensive set of boundary-layer-noise measurements has recently been made on the Lockheed C-141A, a large turbofan aircraft. Data were taken at three external locations on the fuselage and at several altitudes and airspeeds ranging from Mach 0.24 at 2000 ft to Mach 0.80 at 40 000 ft. Due to the lack of standardized methods of boundary-layer-noise prediction, it is felt that analysis of the data would be of interest, since previous similar data have been obtained primarily on much smaller jet aircraft, missiles, and from wind-tunnel studies. The frequency spectra obtained have been generalized and compared with similar data from other aircraft and tests. Generally, good agreement was found with a tendency for somewhat higher levels in the low-frequency range. The ratio of over-all sound pressure to dynamic pressure agrees closely with previous results, averaging approximately 0.006.
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