Wesley CONDREN, Raghul RAVICHANDRAN, Anthony FINNERTY, Chris HAMBIDGE, Matthew MCGILVRAY

DOI Number: 10.60853/w3v7-e356

Conference number: HiSST-2024-00150

This paper presents an experimental study into the combined effects of large scale surface roughness and the transfer of pyrolysis gases that occur on an ablative surface during reentry. The experiments were conducted in the High Density Tunnel at the University of Oxford where a micro-porous transpiration cooled sample, that has been machined to exhibit an idealised two dimensional roughness pattern at its surface, was subjected to a Mach 5 turbulent boundary layer. Spatially resolved heat transfer data was collected utilising infrared thermography (IRT) adapted to account for the three dimensional effects that result from surface roughness. Additionally, pressure sensitive paint was employed to acquire two dimensional surface pressure measurements over the sample, ultimately giving an indication of the drag it experienced. The heat transfer and surface pressure data were collected for blowing parameters spanning 0-1.5, presented as an augmentation factor relative to the smooth, no injection case.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
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