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Blade Tip Pressure Measurements Using Pressure Sensitive PaintThis paper discusses the application of pressure sensitive paint using laser-based excitation for measurement of the upper surface pressure distribution on the tips of rotor blades in hover and simulated forward flight. The testing was conducted in the Rotor Test Cell and the 14- by 22-ft Subsonic Tunnel at the NASA Langley Research Center on the General Rotor Model System (GRMS) test stand. The Mach-scaled rotor contained three chordwise rows of dynamic pressure transducers for comparison with PSP measurements. The rotor had an 11 ft 1 in. diameter, 5.45 in. main chord and a swept, tapered tip. Three thrust conditions were examined in hover, C(sub T) = 0.004, 0.006 and 0.008. In forward flight, an additional thrust condition, C(sub T) = 0.010 was also examined. All four thrust conditions in forward flight were conducted at an advance ratio of 0.35.
Document ID
20120009691
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Wong, Oliver D. (Army Aviation Systems Command Hampton, VA, United States)
Watkins, Anthony Neal (NASA Langley Research Center Hampton, VA, United States)
Goodman, Kyle Z. (ATK Space Systems Hampton, VA, United States)
Crafton, James (Innovative Scientific Solutions, Inc. OH, United States)
Forlines, Alan (Innovative Scientific Solutions, Inc. OH, United States)
Goss, Larry (Innovative Scientific Solutions, Inc. OH, United States)
Gregory, James W. (Ohio State Univ. Columbus, OH, United States)
Juliano, Thomas J. (Ohio State Univ. Columbus, OH, United States)
Date Acquired
August 25, 2013
Publication Date
May 1, 2012
Subject Category
Air Transportation And Safety
Report/Patent Number
NF1676L-13553
Meeting Information
Meeting: American Helicopter Society 68th Annual Forum and Technology Display
Location: Fort Worth, TX
Country: United States
Start Date: May 1, 2012
End Date: May 3, 2012
Funding Number(s)
WBS: WBS 877868.02.07.07.03.02.02
Distribution Limits
Public
Copyright
Public Use Permitted.

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