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Fuselage surface pressure measurements of a helicopter wind-tunnel model with a 3.15-meter diameter single rotorA wind-tunnel investigation was conducted to measure the time averaged fuselage surface pressures of a helicopter model with a 3.15 meter diameter, four-bladed articulated rotor. Measurements were made at hover and advance ratios of 0.05, 0.15, and 0.20 for a range of thrusts. Data are presented with no analysis.
Document ID
19790017844
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Freeman, C. E. (NASA Langley Research Center Hampton, VA, United States)
Mineck, R. E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-80051
Report Number: NASA-TM-80051
Accession Number
79N26015
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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