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Helicopter impulsive noise: Theoretical and experimental statusThe theoretical and experimental status of helicopter impulsive noise is reviewed. The two major source mechanisms of helicopter impulsive noise are addressed: high-speed impulsive noise and blade-vortex interaction impulsive noise. A thorough physical explanation of both generating mechanism is presented together with model and full-scale measurements of the phenomena. Current theoretical prediction methods are compared with experimental findings of isolated rotor tests. The noise generating mechanism of high speed impulsive noise are fairly well understood - theory and experiment compare nicely over Mach number ranges typical of today's helicopters. For the case of blade-vortex interaction noise, understanding of noise generating mechanisms and theoretical comparison with experiment are less satisfactory. Several methods for improving theory-experiment are suggested.
Document ID
19840010982
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Schmitz, F. H. (NASA Ames Research Center Moffett Field, CA, United States)
Yu, Y. H. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1983
Subject Category
Acoustics
Report/Patent Number
NAS 1.15:84390
USAAVRADCOM-TR-83-A-2
A-9477
NASA-TM-84390
Report Number: NAS 1.15:84390
Report Number: USAAVRADCOM-TR-83-A-2
Report Number: A-9477
Report Number: NASA-TM-84390
Accession Number
84N19050
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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