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A flight investigation of performance and loads for a helicopter with 10-64C main rotor blade sectionsA flight investigation produced data on performance and rotor loads for a teetering rotor, AH-1G helicopter flown with a main rotor that had the NLR-1T airfoil as the blade section contour. The test envelope included hover, forward flight speeds from 34 to 83 m/sec (65 to 162 knots), and collective fixed maneuvers at about 0.25 tip speed ratio. The data set for each test point describes vehicle flight state, control positions, rotor loads, power requirements, and blade motions. Rotor loads are reviewed primarily in terms of peak to peak and harmonic content. Lower frequency components predominated for most loads and generally increased with increased airspeed, but not necessarily with increased maneuver load factor. Detailed data for an advanced airfoil on an AH-1G are presented.
Document ID
19800024840
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Morris, C. E. K. (NASA Langley Research Center Hampton, VA, United States)
Tomaine, R. L. (AVRADCOM St. Louis, Mo., United States)
Stevens, D. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
AVRADCOM-TM-80-B-2
NASA-TM-81871
Accession Number
80N33348
Funding Number(s)
PROJECT: RTOP 533-01-43-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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