Raghul RAVICHANDRAN, Luke DOHERTY, Matthew MCGILVRAY

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST2024-00192

This paper presents the modelling and feasibility assessment of using transpiration cooling in the context of active thermal protection systems for hypersonic sharp leading edges. Heat flux reduction effects of transpiration and fim cooling are modelled using semi-empirical correlations from literature, which are corroborated and improved on using high fidelity numerical work. A previously developed numerical tool is used for rapid calculations for temperature of the vehicle substructure. The model was constrained by assessing coolant volumetric requirements, and employing moderate mass injection parameters, due to boundary layer blowoff and pressure drag penalties associated with large mass fluxes. The results show that transpiration cooling may be a viable thermal protection system for long duration trajectories at moderate altitudes and Mach numbers, where ablative and passive systems are not possible.

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In Categories: 1.Events, HiSST 2024, Thermal and Energy Management
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