Pressure Sensitive Paint Measurements on 15% Scale Rotor Blades in Hover

Wong, Oliver D.; Watkins, A. Neal; Ingram, JoAnne L.

doi:10.2514/6.2005-5008

Cited by 21 publications

(19 citation statements)

References 22 publications

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“…The second viewing angle was chosen to collect data from a different azimuthal angle with the vertical separation increased to 1.35 radii, equal to the horizontal separation. A more thorough description of the mounting and measurement regions as well as test conditions is provided in [17].…”

Section: Methodsmentioning

confidence: 99%

Development of a Pressure Sensitive Paint System for Measuring Global Surface Pressures on Rotorcraft Blades

Watkins

Leighty

Lipford

et al. 2007

2007 22nd International Congress on Instrumentation in Aerospace Simulation Facilities

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Abstract-This paper will describe the results from a proof of concept test to examine the feasibility of using Pressure Sensitive Paint (PSP) to measure global surface pressures on rotorcraft blades in hover. The test was performed using the U.S. Army 2-meter Rotor Test Stand (2MRTS) and 15% scale swept rotor blades. Data were collected from five blades using both the intensity-and lifetime-based approaches. This paper will also outline several modifications and improvements that are underway to develop a system capable of measuring pressure distributions on up to four blades simultaneously at hover and forward flight conditions.

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Section: Methodsmentioning

confidence: 99%

Development of a Pressure Sensitive Paint System for Measuring Global Surface Pressures on Rotorcraft Blades

Watkins

Leighty

Lipford

et al. 2007

2007 22nd International Congress on Instrumentation in Aerospace Simulation Facilities

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“…The authors' previous testing has shown that the lifetime-based approach is required to deal with the aeroelastic deformation of the rotor blades 6 . As such, only the lifetime-based technique will be described here.…”

Section: Psp Primermentioning

confidence: 99%

“…Additionally, background images are collected and subtracted from the data images to remove any remaining ambient light and compensate for camera noise. In the previous work by Wong, et al 6,7 , the data images were "built up" from hundreds of exposures (rotor revolutions). For this method to work, the PSP must be excited by the same illumination field for each revolution.…”

Section: Psp Primermentioning

confidence: 99%

“…The tunnel can reach a maximum forward velocity of 348 ft/sec with a dynamic pressure of 144 psf. The Reynolds number per foot ranges from 0 to 2.2 x10 6 . Test section airflow is produced by a 40 ft diameter, 9-bladed fan driven by a 12,000 hp main drive.…”

Section: Fig 3 -Hover Configuration In the Rotor Test Cellmentioning

confidence: 99%

“…Dynamic PSP may enable high resolution pressure measurements on helicopter rotors, thus allowing more accurate analytical prediction methods. Work in this area has been very limited to date [3][4][5][6][7] . Over the last several years, the US Army Aeroflightdynamics Directorate, Joint Research Program Office and the NASA Subsonic Rotary Wing Project have partnered to develop PSP measurement techniques for use on rotor blades.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Blade Tip Pressure Measurements Using Pressure-Sensitive Paint

Wong¹,

Watkins²,

Goodman³

et al. 2018

j am helicopter soc

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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-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 T = 0.004, 0.006 and 0.008. In forward flight, an additional thrust condition, C T = 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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