Mona Karimi & Christian Stemmer

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-377

Planetary entry environment of hypersonic vehicles presents the extreme effects of high-temperature
real-gas. Aeroshell of spacecraft heat shields are made of ablative materials in order to survive such
high-energy environments. Ablation can impact surface heating via injecting pyrolysis gas into the
boundary layer, thus prompt a strong interaction between the surface ablative materials and the boundary layer flow. By means of direction numerical simulation, the current study examines the effect of
blowing at the wall on the aeroheating within the boundary layer subject to the thermochemical effects
of vibrational excitation and dissociation of air mixture in hypersonic chemically reacting flows.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2022
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