New Hypersonic Shock Tunnel at the Laboratory of Aerothermodynamics and Hypersonics Prof. Henry T. Nagamatsu

Journal Article · Mon Apr 28 00:00:00 EDT 2008 · AIP Conference Proceedings

DOI:https://doi.org/10.1063/1.2931888· OSTI ID:21137101

Toro, P G. P.; Minucci, M A. S.; Chanes, Jr, J B; Oliveira, A C; Gomes, F A. A.; Myrabo, L N; Nagamatsu, Henry T ^[1]

---

1. Laboratory of Aerothermodynamics and Hypersonics. Institute for Advanced Studies. IEAv-CTA. Rod. dos Tamoios km 5.5. Putim. Sao Jose dos Campos-SP 12228-001 (Brazil)

The new 0.60-m. nozzle exit diameter hypersonic shock tunnel was designed to study advanced air-breathing propulsion system such as supersonic combustion and/or laser technologies. In addition, it may be used for hypersonic flow studies and investigations of the electromagnetic (laser) energy addition for flow control. This new hypersonic shock tunnel was designed and installed at the Laboratory for of Aerothermodynamics and Hypersonics Prof. Henry T. Nagamatsu, IEAv-CTA, Brazil. The design of the tunnel enables relatively long test times, 2-10 milliseconds, suitable for the experiments performed at the laboratory. Free stream Mach numbers ranging from 6 to 25 can be produced and stagnation pressures and temperatures up to 360 atm. and up to 9,000 K, respectively, can be generated. Shadowgraph and schlieren optical techniques will be used for flow visualization.

• OSTI ID: 21137101
• Journal Information: AIP Conference Proceedings, Vol. 997, Issue 1; Conference: 5. international symposium on beamed energy propulsion, Kailua-Kona, HI (United States), 12-15 Nov 2007; Other Information: DOI: 10.1063/1.2931888; (c) 2008 American Institute of Physics; Country of input: International Atomic Energy Agency (IAEA); ISSN 0094-243X
• Country of Publication: United States
• Language: English

Related Subjects

71 CLASSICAL AND QUANTUM MECHANICS
GENERAL PHYSICS
ABLATION
AIR
COMBUSTION
CONTROL
DESIGN
FLOW VISUALIZATION
HYPERSONIC FLOW
LASER RADIATION
LASERS
NOZZLES
PROPULSION SYSTEMS
SHOCK TUBES