Pietro RONCIONI, Oreste RUSSO, Francesco CASCONE, Marco MARINI, Sara DI BENEDET TO, Marta ALBANO, Roberto BERTACIN

DOI Number: 10.60853/frqj-2k64

Conference number: HiSST-2024-00127

The present paper deals with the aerodynamic and propulsive characterization of a Hypersonic Scramjet System, composed by Launch Vehicle (LV) and Flight demonstrator (SHEV), as part of a research project on experimentation for hypersonic flight and enabling technologies for future high-speed transportation systems, co-funded by CIRA and ASI. The winged rocket-based launch vehicle is conceived to bring at target altitude and velocity the demonstrator vehicle (SHEV) that is a propelled hypersonic in-flight demonstrator posing the challenge of creating, at national level, an aircraft capable of supporting a levelled hypersonic flight thanks to the introduction of a scramjet propulsion system. This paper reports activities that aim to verify the aerodynamic efficiency (L/D = 3÷4) and the aeropropulsive balance (T>D) at Mach = 6÷8 in controlled flight of the demonstrator and the aerodynamic database of the full system composed by the launch vehicle and the above-mentioned demonstrator.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
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