NDLI: Helicopter impulsive noise: theoretical and experimental status

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Helicopter impulsive noise: theoretical and experimental status

Content Provider	NASA Technical Reports Server (NTRS)
Author	Schmitz, F. H. Yu, Y. H.
Copyright Year	1983
Description	The 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.
File Size	11546918
Page Count	105
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19840010982
Archival Resource Key	ark:/13960/t2b903g9d
Language	English
Publisher Date	1983-11-01
Access Restriction	Open
Subject Keyword	Acoustics Impulses Power Spectra Integral Equations Helicopters Vortices Blade-vortex Interaction Noise Prediction Aircraft Rotor Aerodynamics Noise Generators Blade Slap Noise Aeroacoustics Rotary Wings Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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