High-Speed Pressure Sensitive Paint Measurements of the Initial Concept 3.X Vehicle at Mach 7

Dhanagopal, Abinayaa; Williamson, Chad; LaLonde, Elijah; Gutierrez, Sofia; Andrade, Angelina; Delgado, Valeria; Combs, Christopher S.

doi:10.2514/6.2023-1179

Cited by 3 publications

(3 citation statements)

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“…Closer investigations using high-speed Schlieren on the ogive and the fin-body interface are elaborated in the latter sections. The average temperature maps obtained strongly resemble the PSP pressure maps reported in [37], indicating the coupled nature of the pressure and temperature fluctuations experienced on the model. The overall temperature distribution across the model reveals elevated temperature zones in the nose, which is the stagnation region and hence experiences the highest amount of heating.…”

Section: Mean Surface Temperaturesupporting

confidence: 65%

“…However, the surface of the painted TSP model in this case is expected to be comparable to the model surface coated with PSP. Based on estimates obtained during PSP calibration [37], the thickness of the paint layer on the model is expected to vary between 8 and 50 µm, which is on par with the surface intrusion that occurs when inserting a Kulite or other probes to obtain in situ measurements on the model. According to the material trade and sizing optimization studies conducted by Witeoff and Neergaard [32], the IC3X monocoque composed of titanium alloy is expected to have a skin thickness in the order of 1.3 to 3.1 mm.…”

Section: Fast-tsp Preparation and Applicationmentioning

confidence: 99%

“…This geometry is of particular interest to the hypersonic community and has been the focus of multiple studies in the literature in recent years for hypersonic aeroelasticity [18,22,23] and aerothermodynamics [24][25][26]. This paper presents a comprehensive thermal evaluation of the model carried out in the current experimental campaign [27]. Global heat flux and heat transfer coefficient maps are obtained, in addition to a time series analysis of the temperature distribution along the model.…”

Section: Introductionmentioning

confidence: 99%

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Thermal Evaluation of the Initial Concept 3.X Vehicle at Mach 7

Dhanagopal,

Strasser,

Andrade

et al. 2024

Energies

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High-speed global surface temperature distributions and heat flux measurements on the Initial Concept 3.X vehicle (IC3X) model were investigated at the UTSA Mach 7 wind tunnel, examining angles of attack of 0° and 5° at a freestream unit Reynolds number (Re) ~7 × 106 m−1. A ruthenium-based, fast-responding, temperature-sensitive paint (fast-TSP) prepared in-house was applied to a 7.1% scale model of the vehicle. Static calibration was performed to convert the intensity measurements into surface temperature values. The surface temperatures and derived heat flux fields conformed to the predicted trends, which was corroborated by Schlieren flow visualization. Notably, the average surface temperature variation was identified to range from 6 to 34 K at a 0° angle of attack and from 11 to 44 K at a 5° angle of attack, with the most pronounced gradient detected at the stagnation point. Additional measurements provided a detailed thermal assessment of the model, including estimations of the stagnation point heat flux, the convective heat transfer coefficient, and the modified Stanton number. Statistical and time series analyses of the data collected revealed the absence of prevailing unsteady phenomena, suggesting that the tested design geometry is well suited for hypersonic flight applications. These experimental outcomes not only shed light on the aerothermodynamics experienced during high-speed flight but also underscore the effectiveness of fast-TSP in capturing both quantitative and qualitative thermal data.

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Section: Mean Surface Temperaturesupporting

confidence: 65%

Section: Fast-tsp Preparation and Applicationmentioning

confidence: 99%