宇宙機研究のための小型自由ピストン型高エンタルピ衝撃風洞の開発

概要

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A Small-Scale Free Piston Type High Enthalpy Shock Tunnel has been developed at the Aeronautical and Space Engineering Division of Mechanical Systems Engineering in Muroran Institute of Technology for the study of hypersonic and high enthalpy flow being essential for space plane. By employing this shock tunnel, obtained free stream Mach number and total pressure were about 8 and 0.03MPa, respectively. The flow duration was about 1ms and estimated flow enthalpy was about 3MJ/kg. Photographs taken by CCD camera showed the developing shock wave and the shape of radiating region around the model. And also, the interaction of the hypersonic flow and sonic jet injected normally into free stream was observed. The future works such as the real gas effect problems, supersonic combustion in high enthalpy flow and so on, which are related to space plane development, will be able to be conducted using this high enthalpy facility.
室蘭工業大学の論文
1999-11-30