Flow Characteristics of the New Mach 4 Supersonic Wind Tunnel of Muroran Institute of Technology and Study on Shock Wave and Turbulent Boundary Layer Interactions
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, Mach4.0 and 2.0) was designed and constructed in Muroran Institute of Technology (MIT). This paper describes the flow characteristics of the Mach 4 and 2 supersonic wind tunnel and the experimental study on the shock wave and turbulent boundary layer interactions (pseudo-shock wave, or PSW) in a rectangular duct, using the MIT supersonic wind tunnel.
室蘭工業大学新設マッハ4超音速風洞の気流特性および衝撃波と乱流境界層の干渉現象に関する研究
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