Overview of JAXA 1.27m Hypersonic Wind Tunnel - Facility for Future Hypersonic Transport Technology
نویسندگان
چکیده
منابع مشابه
Development of a Pilot Model of Hypersonic Rarefied Wind-Tunnel
A pilot model of the hypersonic rarefied wind-tunnel (HRWT) has been developed and its flow characteristics have been measured. The HRWT consists of a gas heater which produces an increase in working gas temperature, an expansion nozzle with a large expansion ratio, a vacuum chamber as the test section, and an evacuation system with high exhaust velocity to allow a continuous operation at low a...
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This paper presents steady-state (viscous) and timeaccurate (inviscid) numerical solutions of the flowfield inside the Virginia Tech Hypersonic Wind Tunnel (VTHST) with a Mach 4 nozzle. The numerical solutions are obtained using a computational fluid dynamics (CFD) solver named GASP. Comparisons between the steady-state CFD solutions and available experimental data are also presented in this pa...
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The feasibility of digital holographic interferometry using a CW laser @ 532 nm and a Photron APX camera is demonstrated in the F4-ONERA hypersonic wind tunnel. This optical technique is used to point out the possible combustion of a small hydrogen jet in the shock layer developed on the model. The optical technique generates in the field under analysis, interference micro-fringes which are use...
متن کاملDevelopment of a Pulsed Arc Heater for a Hypersonic High Enthalpy Wind Tunnel
A pulsed arc heater was designed and manufactured at Centrospazio to equip a new hypersonic high-enthalpy blow-down wind tunnel capable of producing flows with a specific total enthalpy up to 2.5 MJ/kg. The heater mainly consists of two coaxial electrodes, separated by a constrictor, and a plenum chamber. The flow is heated by an electric arc ignited between the electrodes and sustained by the ...
متن کاملInviscid Design of Hypersonic Wind Tunnel Nozzles for a Real Gas
A straightforward procedure has been developed to quickly determine an inviscid design of a hypersonic wind tunnel nozzle when the test gas is both calorically and thermally imperfect. This real gas procedure divides the nozzle into four distinct parts: subsonic, throat to conical, conical, and turning flow regions. The design process is greatly simplified by treating the imperfect gas effects ...
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ژورنال
عنوان ژورنال: Marine Engineering
سال: 2013
ISSN: 1346-1427,1884-3778
DOI: 10.5988/jime.48.807