Spatially Nonuniform Self-Quenching of the Pressure-Sensitive Paint PtTFPP/FIB

Ruyten, Wim; Sellers, Marvin E.; Afb, Arnold; Baker, Wink

doi:10.2514/6.2009-1660

Cited by 21 publications

(8 citation statements)

References 9 publications

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“…However, the chosen paint formulation (the porous polymer) displays a significant change in performance that is tied to the application process. This phenomenon has been observed previously in many PSP formulations [26][27][28] but is very pronounced in this formulation. Essentially, the excited state lifetime of the Pt(TfPP) shows heterogeneity with application, where the lifetime can change dramatically based on the relative localized concentration of the probe.…”

Section: E Data Analysissupporting

confidence: 81%

Deployment of a Pressure Sensitive Paint System for Measuring Global Surface Pressures on Rotorcraft Blades in Simulated Forward Flight

Watkins

Leighty

Lipford

et al. 2012

28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference

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This paper will present details of a Pressure Sensitive Paint (PSP) system for measuring global surface pressures on the tips of rotorcraft blades in simulated forward flight at the 14-by 22-Foot Subsonic Tunnel at the NASA Langley Research Center. The system was designed to use a pulsed laser as an excitation source and PSP data was collected using the lifetime-based approach. With the higher intensity of the laser, this allowed PSP images to be acquired using a single laser pulse, resulting in the collection of crisp images that can be used to determine blade pressure at a specific instant in time. This is extremely important in rotorcraft applications as the blades experience dramatically different flow fields depending on their position. Testing of the system was performed using the U.S. Army General Rotor Model System equipped with four identical blades. Two of the blades were instrumented with pressure transducers to allow for comparison of the results obtained from the PSP. Preliminary results show that the PSP agrees both qualitatively and quantitatively with both the expected results as well as with the pressure transducers. Several areas of improvement have been indentified and are currently being developed for future testing.

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Section: E Data Analysissupporting

confidence: 81%

Deployment of a Pressure Sensitive Paint System for Measuring Global Surface Pressures on Rotorcraft Blades in Simulated Forward Flight

Watkins

Leighty

Lipford

et al. 2012

28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference

View full text Add to dashboard Cite

show abstract

“…Prior to acquiring PSP images at run conditions, a correction was performed to account for paint application inconsistencies and dye inhomogeneity in the PSP coating. This was done by acquiring wind-off images at different pressures in the facility, encompassing the expected pressure range throughout the wind-on testing [19,20]. A single static pressure tap on both noses was used to anchor the PSP measurements.…”

Section: A Psp Setupmentioning

confidence: 99%

Space Launch System Booster Separation Supersonic Powered Testing with Surface and Off-body Measurements

Winski

Danehy

Watkins

et al. 2019

AIAA Scitech 2019 Forum

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A wind tunnel test was run in the NASA Langley Unitary Plan Wind Tunnel simulating the separation of the two solid rocket boosters (SRB) from the core stage of the NASA Space Launch System (SLS). The test was run on a 0.9% scale model of the SLS Block 1B Cargo (27005) configuration and the SLS Block 1B Crew (28005) configuration at a Mach of 4.0. High pressure air was used to simulate plumes from the booster separation motors located at the nose and aft skirt of the two boosters. Force and moment data were taken on both SRBs and on the core stage. Schlieren still photos and video were recorded throughout testing. A set of points were acquired using Cross-correlation Doppler Global Velocimetry (CCDGV) readings to get 3 component velocity measurements between the core and the left-hand SRB. The CCDGV laser was utilized to record flow visualization in the same location, between the core and the left-hand SRB. Pressure Sensitive Paint data were taken on a separate set of runs. Computational Fluid Dynamics (CFD) runs were computed on a subset of the wind tunnel data points for comparison. A combination of the force/moment, CCDGV and Pressure Sensitive Paint (PSP) data (as well as schlieren images) at the CFD-specified test conditions will be used to validate the CFD simulations that will be used to build an SLS booster separation database at flight conditions.Notice to the Reader -The Space Launch System, including its predicted performance and certain other features and characteristics, has been defined by the U.S. Government to be Sensitive But Unclassified (SBU). Information deemed to be SBU requires special protection and may not be disclosed to an international audience. To comply with SBU restrictions, details such as absolute values have been removed from some plots and figures in this paper. It is the opinion of the authors that despite these alterations, there is no loss of meaningful technical content.

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“…In order to correct for inhomogeneous lifetime distribution over the model surface each parameter is normalized by the reference condition [7,9]. Figure 6 shows the normalized plot of each parameter by the reference condition at P ref = 60 kPa and T ref = 303 K. Figure 7 shows pressure sensitivities of both parameters at T = 303 K. The phase angle shows higher sensitivity compared to the demodulation index, especially at higher pressure range.…”

Section: Resultsmentioning

confidence: 99%

Investigation of Image-based Lifetime PSP Measurements with Sinusoidal Excitation Light

Yorita

Henne

Klein

et al. 2019

AIAA Scitech 2019 Forum

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The applicability of frequency-domain fluorescence lifetime imaging (FLIM) with a newly developed CMOS camera sensor (pco.flim) to Pressure-Sensitive Paint (PSP) measurements in wind tunnel tests was investigated. Two lifetime parameters, the phase angle and demodulation index, can be used as a function of pressure in FLIM technique. First, the characteristics of FLIM-PSP technique were examined in calibration tests. The two lifetime parameters, a phase shift and a modulation index, show different sensitivity to pressure and temperature. This indicates a potential of simultaneous pressure and temperature measurement of the FLIM-PSP technique. Next, the FLIM-PSP technique is demonstrated in a transonic wind tunnel using a delta-wing model. The obtained PSP results successfully visualize the complex pressure distribution on the model surface and the quantitative agreement with conventional pressure tap data is good.

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Spatially Nonuniform Self-Quenching of the Pressure-Sensitive Paint PtTFPP/FIB

Cited by 21 publications

References 9 publications

Deployment of a Pressure Sensitive Paint System for Measuring Global Surface Pressures on Rotorcraft Blades in Simulated Forward Flight

Deployment of a Pressure Sensitive Paint System for Measuring Global Surface Pressures on Rotorcraft Blades in Simulated Forward Flight

Space Launch System Booster Separation Supersonic Powered Testing with Surface and Off-body Measurements

Investigation of Image-based Lifetime PSP Measurements with Sinusoidal Excitation Light

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