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A flight investigation of blade-section aerodynamics for a helicopter main rotor having 10-64C airfoil sectionsPressure data at 90 percent blade radius were obtained for a helicopter main rotor with 10-64C blade sections during flight. Concurrent measurements ere made of vehicle flight state, performance and some rotor loads. The test envelope included hover, level flight from about 65 to 162 knots, climb and descent, and collective fixed maneuvers. Good agreement is shown between some sets of airfoil pressure distributions obtained in flight and those from two-dimensional wind-tunnel tests or theoretical calculations.
Document ID
19820006185
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Morris, C. E. K., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-83226
Accession Number
82N14058
Funding Number(s)
PROJECT: RTOP 530-14-13-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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