Luiz H. M. S. Soares, Pedro P. B. Araujo, Rafael B. C. Facchin, Ramon Carneiro, Paulo G. P. Toro, Angelo Passaro

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-245

Hypersonic air-breathing propulsion and supersonic combustion is a research field that has been
explored either for military and civilian applications.Developing technologies to achieve airbreathing
hypersonic flight involves challenges in different areas. Three problems related to scramjet engine
design are addressed in the present paper. Stochastic computational techniques are utilised to optimise
the total pressure recovery, considering two different inlet geometries, 2D planar and Bussenann
geometry, the uninstalled thrust, and the geometry of the combustion chamber to keep constant the
internal pressure considering heat addition. Partial results are presented for the three problems
considered. It is an ongoing study to optimise the performance of a scramjet at the conceptual and
pre-design phase using metaheuristics and semi-empirical methodologies, leading to a more robust
result to be explored in CFD computations.

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In Categories: 1.Events, HiSST 2022, Propulsion Systems and Components
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