Design and Preliminary Calibration of the UTSA Mach 7 Hypersonic Ludwieg Tube

Bashor, Ian; Hoffman, Eugene N.; Gonzalez, G.J.; Combs, Christopher S.

doi:10.2514/6.2019-2859

Cited by 8 publications

(4 citation statements)

References 2 publications

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“…Finally, comparisons of boundary layer mapping via several techniques (PIV, MTV, Pitot probe scans, and CFD) showed a good agreement between the multiple techniques employed. Based on the facility characterization, the use of CFD in the design of this facility [35] has proven to be a robust and useful tool.…”

Section: Comparison Of Experimental and Cfd Resultsmentioning

confidence: 99%

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Flow Characterization of the UTSA Hypersonic Ludwieg Tube

et al. 2023

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The characterization of a hypersonic impulse facility is performed using a variety of methods including Pitot probe scans, particle image velocimetry, and schlieren imaging to verify properties such as the velocity, Mach number, wall boundary layer thickness, and freestream turbulence intensity levels. The experimental results are compared to the numerical simulations of the facility performed with Ansys Fluent to compare the design and operational conditions. The presentation of results in this manuscript is prefaced by a description of the facility and its capabilities. The UTSA Ludwieg tube facility can produce a hypersonic freestream flow with a Mach number of 7.2 ± 0.2 and unit Reynolds numbers of up to 200 × 106 m−1. The Pitot probe profiles of the 203-mm-square test section indicate a 152 ± 10 mm square freestream core with turbulence intensity values ranging from 1% to 2%. Schlieren imaging of the oblique shockwaves on a 15° wedge model provided an alternate means of verifying the Mach number. Particle image velocimetry and previous molecular tagging velocimetry results showed a good agreement with the Pitot probe data and numerical simulations in the key parameters including freestream velocity, wall boundary layer velocity profiles, and wall boundary layer thickness.

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Section: Comparison Of Experimental and Cfd Resultsmentioning

confidence: 99%

“…A 6 m 3 (1600 gallon) vacuum tank is used with the facility to achieve the desired number of steady-state passes and test duration. An indepth discussion of this facility, the motivation behind the various design choices, and a detailed discussion of the individual components are provided by Bashor et al [35], and Hoffman et al [36,37].…”

Section: Methodsmentioning

confidence: 99%

Flow Characterization of the UTSA Hypersonic Ludwieg Tube

et al. 2023

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“…The freestream velocity was found to be 885 m/s [21]. A detailed description of this facility's design, construction, and capabilities is presented by Bashor et al [28] and Hoffman et al [29][30][31]. A summary of the test conditions for the experimental campaign is provided in Table 1.…”

Section: Wind Tunnelmentioning

confidence: 99%

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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“…The duration of each test in this facility is approximately 450 ms, consisting of multiple steady-state passes lasting 50 to 100 ms each [28]. A more comprehensive description of the facility's design and capabilities can be found in the works of Bashor et al [30] and Hoffman et al [31].…”

Section: Experimental Facilitymentioning

confidence: 99%

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

Delgado Elizondo,

Dhanagopal,

Combs

2023

Aerospace

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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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Design and Preliminary Calibration of the UTSA Mach 7 Hypersonic Ludwieg Tube

Cited by 8 publications

References 2 publications

Flow Characterization of the UTSA Hypersonic Ludwieg Tube

Flow Characterization of the UTSA Hypersonic Ludwieg Tube

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

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

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