Blade Tip Pressure Measurements Using Pressure Sensitive Paint
作者： Oliver D. Wong , A. Neal Watkins , Kyle Z. Goodman , Jim Crafton , Alan Forlines
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摘要: This paper discusses the application of pressure sensitive paint using laser-based excitation for measurement upper surface distribution on tips rotor blades in hover and simulated forward flight. The testing was conducted Rotor Test Cell 14- by 22-ft Subsonic Tunnel at NASA Langley Research Center General Model System (GRMS) test stand. Mach-scaled contained three chordwise rows dynamic transducers comparison with PSP measurements. had an 11 ft 1 in. diameter, 5.45 main chord a swept, tapered tip. Three thrust conditions were examined hover, C(sub T) = 0.004, 0.006 0.008. In flight, additional condition, 0.010 also examined. All four flight advance ratio 0.35.
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