Application of Pressure-Sensitive Paint to Investigate Hypersonic Shock-Wave/ Boundary-Layer Interactions

Andrade, Angelina; LaLonde, Elijah; Hoffman, Eugene N.; Gutierrez, Sofia; Combs, Christopher S.

doi:10.2514/6.2023-1178

Cited by 3 publications

(3 citation statements)

References 18 publications

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“…During hypersonic flight, high-speed aircraft or spacecraft experiences high-pressure and high-temperature loads on their surfaces and inlets due to the shock wave/boundary layer interaction (SWBLI). The flow conditions in the boundary layer undergo significant changes in temperature and pressure, posing a significant safety threat to the aircraft [1]. In SWBLI research, the ramp model serves as a typical experimental test model and is widely used in various applications such as control surfaces, inlets, and wings [2,3].…”

Section: Introductionmentioning

confidence: 99%

“…The observation of Görtler vortices began with Miller's [9] use of the oil-streak technique, and subsequently, researchers classically observed the footprints of the flow structures on the model surface [10][11][12][13][14][15] or they used physical probes [16][17][18] to obtain flow field information. Alternatively, high-speed visualization [7,19] was performed to acquire qualitative data about the flow structure.…”

Section: Introductionmentioning

confidence: 99%

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WITHDRAWN: Visualization of Görtler vortices in high–enthalpy plasma flow using planar laser-induced fluorescence

Yu,

Yuan,

Peng

et al. 2024

Preprint

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The Görtler vortices phenomenon is a characteristic flow feature observed in the boundary layer of the compressed ramps in hypersonic flow. In the context of high-enthalpy plasma flow during aerospace re-entry processes, there is currently a lack of effective means to visualize Görtler vortices of the boundary layer. In this study, the nitric oxide planar laser-induced fluorescence (NO PLIF) technique was employed to visualize the boundary layer of a ramp in a 50 MW arc-heated wind tunnel. The Görtler-like vortex structures were observed in the boundary layer of the ramp. This is the first time that Görtler vortices have been clearly observed in high-enthalpy plasma flow. Through varying the flow conditions, it was found that Görtler vortices persisted in the boundary layer of the ramp when the total enthalpy of the arc-heated wind tunnel exceeded 12.3 MJ/kg. And the position of the Görtler streaks was found to be non-fixed, while the average Görtler wavelength remained approximately 30 mm at 10° ramp and showed limited variation with the total enthalpy. Additionally, a sheet forming optics system with adjustable angle and height was designed to enable visualization of Görtler vortices in the boundary layer of the ramp at different angles and heights. The vortex structures on low-angle ramp exhibit better stability and shorter wavelength. Meanwhile, the visualization results at different heights have confirmed that the wavelength of the Görtler vortices is approximately equal to the boundary layer thickness. This work demonstrates the feasibility and potential of the PLIF technique in visualization of the boundary layer in plasma flow, especially in regard to the Görtler vortices.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

WITHDRAWN: Visualization of Görtler vortices in high–enthalpy plasma flow using planar laser-induced fluorescence

Yu,

Yuan,

Peng

et al. 2024

Preprint

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“…The prepared paint was found to respond to pressure changes at Mach 7.2, and the coherence of the spectra, as shown in Figure 7, was calculated to compare the similarity of the signals at different frequencies. It was found that, on a canonical wall-to-wall flatplate model, the paint exhibited a ~7 kHz response rate with a 68% coherence to Kulite transducers, as reported in [39].…”

Section: Static Calibration Curvementioning

confidence: 54%

Fast-Responding Pressure-Sensitive Paint Measurements of the IC3X at Mach 7.2

Delgado Elizondo,

Dhanagopal,

Combs

2023

Aerospace

Self Cite

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Global surface pressure measurements of a 5.7% scale AFRL Initial Concept 3.X vehicle (IC3X) were obtained using a fast-responding ruthenium-based pressure-sensitive paint (PSP) at the UTSA Mach 7 Ludwieg Tube Wind Tunnel at two different angles of attack, 0° and 2.5°. Static calibration of the paint was performed over a range of 0.386 kPa to 82.7 kPa to relate luminescent intensity to pressure. Details on the facility, paint preparation, application, calibration, and image processing techniques are provided in the manuscript. The results from statistical, spectral, and proper orthogonal decomposition (POD) analyses are presented to characterize the pressure field observed on the model. The experimental results qualitatively follow the expected trends and correspond to the occurrence of shock waves and expansion fans, which were visualized via Schlieren imaging. The theoretical pressure range obtained from conical shock analysis for 0° agrees with the experimentally derived pressure range for the model, and the outliers are attributed to errors in image registration. This study presents preliminary pressure measurements that pave the way for obtaining time-resolved global PSP measurements to train and validate aerothermodynamic machine learning models.

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Optical and Surface Pressure Measurements on an Angled Wedge in Mach 4 Freestream

Smith,

Lester,

Kreth

2024

AIAA SCITECH 2024 Forum

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Application of Pressure-Sensitive Paint to Investigate Hypersonic Shock-Wave/ Boundary-Layer Interactions

Cited by 3 publications

References 18 publications

WITHDRAWN: Visualization of Görtler vortices in high–enthalpy plasma flow using planar laser-induced fluorescence

WITHDRAWN: Visualization of Görtler vortices in high–enthalpy plasma flow using planar laser-induced fluorescence

Fast-Responding Pressure-Sensitive Paint Measurements of the IC3X at Mach 7.2

Optical and Surface Pressure Measurements on an Angled Wedge in Mach 4 Freestream

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