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An experimental investigation of the effect of rotor tip shape on helicopter blade-slap noiseThe effect of tip-shape modification on blade-vortex interaction-induced helicopter blade-slap noise was investigated. The general rotor model system (GRMS) with a 3.148 m (10.33 ft) diameter, four-bladed fully articulated rotor was installed in the Langley V/STOL wind tunnel. The tunnel was operated in the open-throat configuration with treatment to improve the semi-anechoic characteristics of the test chamber. Based on previous investigation, four promising tips (ogee, sub-wing, 60 deg swept-tapered, and end-plate) were used along with a standard square tip as a baseline configuration. Aerodynamic and acoustical data concerning the relative applicability of the various tip configurations for blade-slap noise reduction are presented without analysis or discussion.
Document ID
19790017673
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Hoad, D. R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1979
Subject Category
Acoustics
Report/Patent Number
NASA-TM-80066
Accession Number
79N25844
Funding Number(s)
PROJECT: RTOP 505-10-23-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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