28th Congress of the International Council of the Aeronautical Sciences, 23 - 28 September 2012, Brisbane, Australia
Paper ICAS 2012-3.8.3

STUDY OF RADIATIVE HEAT TRANSFER IN TITAN ATMOSPHERIC ENTRY

H. Porat, R. G. Morgan, T. J. McIntyre
Univ. of Queensland, Australia

Keywords: re-entry, radiation, hypervelocity, ablation

A Titan atmospheric test gas is used to create a flow over a cylindrical model, with shock speed of 6.5 km/s. The radiating species in the shock layer and the radiative heat flux on the surface of the cylinder are measured by emission spectroscopy and radiation gauges, respectively.

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