衝撃波を伴う超音速内部流動に関する研究(超音速内部流動実験装置の開発およびマッハ数2と4の擬似衝撃波の特性)(流体工学,流体機械)

概要

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In order to investigate the supersonic flow phenomena related to internal and external flows of high-pressure gas pipeline systems, new air breathing engines and space planes, a new supersonic wind tunnel (pressure-vacuum type, Mach 2.0 and 4.0) was designed and constructed in Muroran Institute of Technology. The cross section of the test section is 8 × 8 cm^2, and the working-time of the wind tunnel is 20 s for Mach 4 condition. This paper describes firstly outlines of the new Mach 4 supersonic wind tunnel, and describes secondly the structure and characteristics of the Mach 2 and 4 supersonic flows with pseudo-shock waves in a square duct. The characteristics of the pseudo-shock waves were clarified by color schlieren photographs and duct wall pressure measurements.
社団法人日本機械学会の論文
2002-12-25