Hypersonic Low Temperature Ablation an Experimental Study of Cross-Hatched Surface Patterns

Stock, H. W.; Ginoux, Jean J.

doi:10.1007/978-94-010-2559-1_9

Cited by 3 publications

(1 citation statement)

References 7 publications

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“…Materials used in previous studies are not well-suited for liquid ablation experiments in shock tunnels. Naphthalene [13] and camphor [14] made of water ice [8] or CO2 ice [9] melt and also evaporate during the test preparation.…”

Section: B Low Temperature Ablating Metalmentioning

confidence: 99%

Experimental Investigation of Thermal Ablation by Melting in a Hypersonic Shock Tunnel

Denis¹,

Hruschka²,

Bastide³

et al. 2022

Journal of Spacecraft and Rockets

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In this paper a novel approach for the experimental measurement of the ablation by melting is presented. The experiments are carried out with a hypersonic shock tunnel. The tested models are made of gallium, which melts at low temperatures, allowing the generation and then the measurement of the ablation profiles within only two milliseconds. By means of an optical visualization, the model surface changes are recorded during the experiment. An image post-processing algorithm computes the ablation profiles. The results for two hemisphere-cone models and one hemisphere-cylinder model in a Mach 4.5 nitrogen flow are presented. It is found that the maximum ablation occurs at an angular position of around 30 degrees off-axis rather than at the stagnation point. This is most likely a consequence of the laminar-turbulent transition on the model forebody. Nomenclature Cp= Heat capacity at constant pressurenumber [−] P = Pressure [Pa] or Power flux [W • m −2 ] Re = Reynolds number [−] Re/x = Reynolds number per meter [m −1 ]

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