Abstract
For decades, researchers have pursued the development of supersonic combustion ramjet (scramjet) engines. The scramjet is an airbreathing hypersonic propulsion system that utilizes atmospheric oxygen for combustion. Hence, the oxidizer does not have to be carried on-board, which makes scramjets more efficient than rockets and thus very attractive for hypersonic transportation or access-to-space systems. However, hypersonic speeds cause, amongst other challenges, very short residence times within the scramjet combustor. Therefore, achieving a high combustion efficiency poses a major challenge. The combustion efficiency is closely coupled with the mixing efficiency, since most scramjets are mixing limited. Thus, extensive studies focusing on mixing enhancement have been conducted in the past. Different injector shapes and angles [1, 2], flame holding devices [3] and mixing enhancing hypermixers [4] have been investigated in scramjets.
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Gehre, R.M., Peterson, D., Wheatley, V., Boyce, R.R. (2015). Numerical Investigation of the Mixing Process in Inlet-fuelled Scramjets. In: Bonazza, R., Ranjan, D. (eds) 29th International Symposium on Shock Waves 2. ISSW 2013. Springer, Cham. https://doi.org/10.1007/978-3-319-16838-8_32
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DOI: https://doi.org/10.1007/978-3-319-16838-8_32
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