L. M. Vialta , P. A. S. Matos, L. G. Barreta, D. Carinhana Jr.
DOI Number XXX-YYY-ZZZ
Conference Number HiSST-2022-248
The development of hypersonic airbreathing propulsion systems, such as scramjet engines, represents
a great technological challenge, mainly due to the complex aerothermodynamic processes observed
during the flight within the sensible atmosphere. With the advent of new computers and more
sophisticated programs, the design and evaluation of performance in virtual environments has assumed
a mandatory character over the past two decades. However, considering the complete cycle of
technological readiness, in loco evaluation, concerning direct and indirect measurements of parameters
associated with the exposure both systems and subsystems to hypersonic flight conditions, are also
essential steps for innovative projects. Hence, the relevant role that the ground test devices present in
the state-of-art researches is the mitigation of major risks associated to the expensive in-flight tests of
the integrated systems. Thus, the present work had as objective the characterization of flows produced
in the T2 Hypersonic Shock Tunnel installed at Institute of Advanced Studies, IEAv. Flow velocities were
determined by the laser-induced fluorescence velocimetry, LIF, of NO species intrinsically formed and
available at free-stream conditions. Results showed a reasonable agreement between experimentally
and theoretical velocity values, ca. 5%.