A Divergent Shock Tube for Obtaining Supersonic Flows

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概要

• 論文の詳細を見る

• A shock tube having a divergent low pressure chamber just downstream of a partition diaphragm is presented as a simple method for obtaining supersonic flows of fairly high Mach numbers. Flow character in the divergent channel is examined both theoretically and experimentally. Interferometric studies of the flow past a double-wedge profile are presented for Mach numbers of 4.0 and 6.0. At M=6.0, pressure distribution on the wedge surface deviates considerably from theory due to the thickening of the boundary layers

• 社団法人日本物理学会の論文
• 1956-04-05

著者

• Tamaki Fumio

  Institute Of Industrial Science University Of Tokyo

関連論文

• Flash X-Ray Radiography for the Density Measurement in a Hypersonic Air Flow
• Experimental Studies on the Stability of the Transonic Flow past Airfoils
• Some Experiments on Probe Characteristics in Drifting Plasma
• A Divergent Shock Tube for Obtaining Supersonic Flows
• Studies on the Hypersonic Flow Using a Double-Diaphragm Shock Tube

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