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Blade Tip Pressure Measurements Using Pressure-Sensitive Paint

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This 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-Foot Subsonic Tunnel at the NASA Langley Research Center on the General Rotor Model System test stand. The Mach-scaled rotor contained three chordwise rows of dynamic pressure transducers for comparison with pressure-sensitive paint measurements. The rotor had an 11.08 ftdiameter, 5.45 inch main chord, and a swept, tapered tip. Three thrust conditions were examined in hover, CT = 0.004, 0.006, and 0.008. In forward flight, an additional thrust condition, CT = 0.010, was also examined. All four thrust conditions in forward flight were conducted at an advance ratio of 0.35.
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Document Type: Research Article

Publication date: 01 January 2018

This article was made available online on 04 January 2018 as a Fast Track article with title: "Blade Tip Pressure Measurements Using Pressure-Sensitive Paint".

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  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

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