Oreste RUSSO, Antonio FILOSA, Pietro RONCIONI, Marco MARINI, Vincenzo PAOLELLA, Sara DI BENEDETTO, Pasquale NATALE, Giovanni COPPOLA, Francesco BATTISTA, Giuliano RANUZZI, Marta ALBANO, Friedolin STRAUSS

DOI Number: N/A

Conference number: HiSST-2025-276

The paper describes the main challenges involved in designing and testing the combustor of the Scramjet Hypersonic Experimental Vehicle (SHEV). The work is part of an Italian national project co-funded by the national research program PRO.R.A. and the Italian Space Agency (ASI). The comparison of experimental results from wind tunnel tests with CFD simulations will allow us to validate the numerical methodology employed. This approach can then be applied to aero-propulsive evaluation, in order to verify the scramjet engine’s thrust.

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In Categories: 1.Events, 1.HiSST 2025, Propulsion Systems & Components
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