Experimental Investigation of Transitional, Sharp-Fin-Induced Shock-Wave/Boundary-Layer Interactions at Mach 6

Maszkiewicz, Samuel A.; Gillespie, Graeme; Laurence, Stuart J.

doi:10.2514/6.2022-1818

Cited by 6 publications

(2 citation statements)

References 32 publications

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“…In the present work a new FLDI approach [9] for investigating the boundary layer on a flat plate is presented, which was also applied by Maszkiewicz et al [10]. By integrating a glass window into a flat plate (Fig.…”

Section: Introductionmentioning

confidence: 99%

Wall-Normal Focused Laser Differential Interferometry

Lunte,

Schülein

2024

AIAA Journal

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A new approach for measuring boundary-layer disturbances with focused laser differential interferometry (FLDI) for planar models is presented. By integrating a glass window into a flat plate, the optical axis was aligned normal to the model surface, and the focal plane was set inside the boundary layer. By determining the extent of the sensitive volume along the optical axis and calculating the analytical transfer function of the setup, the implications of the FLDI properties on the measured data are analyzed. Measurements performed on a flat plate at Mach 6 are used to demonstrate the effects of the laminar–turbulent transition on the spectral distribution of the power density and to explicitly verify the detectability of the expected second-mode instabilities. Advantages and disadvantages of the proposed setup compared to the conventional one are discussed.

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Section: Introductionmentioning

confidence: 99%

Wall-Normal Focused Laser Differential Interferometry

Lunte,

Schülein

2024

AIAA Journal

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“…Furthermore, TSP has been instrumental in investigating intricate aerodynamic phenomena, including shock wave/boundary-layer interactions and boundary-layer transitions [7] through surface temperature changes on different models, such as cylinders [6,8], compression ramps [9], cones [10][11][12][13], and sharp fins [14]. The operating principle of TSP is sufficiently documented in the literature [15] and is, therefore, only briefly described here.…”

Section: Introductionmentioning

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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