Thiago L Assunção, Marco A. S. Minucci, Lucas A. G. Ribeiro, Pedro. A. S. Matos, Vanessa V. Souza

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-387

This work presents the results of a parametric study carried out at Hypersonic and Aerothermodynamic
Laboratory (LAH), employing the Hypersonic Shock Tunnel T1 with a Shock Tube configuration. A
computational routine was created using Octave program in order to calculate the flow proprieties
under assumption of the calorically perfect gas. Moreover, several Tunnel conditions were analyzed,
where 3 experiments (runs) were carried out for each one. Then, the theoretical results were compared
to experimental data, such as incident Mach number (Ms) and stagnation pressure (p5), providing the
“loss factor” associated to Tunnel T1 operation. Moreover, still concerning this analysis, it was evaluated
the influence of the Driver gas and pressure ratio p4/p1 on the flow proprieties, where the results globally
agree with literature. Finally, a statistical approach was employed in order to evaluate the repeatability
of the results provided by device operation, based on dispersion analysis of the stagnation pressure,
where it was possible to notice a low dispersion of the data.

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In Categories: 1.Events, High-Speed Missions and Vehicles, HiSST 2022
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