204 超音速矩形ダクト内の衝撃波と境界層の干渉 : 衝撃波列の PIV 計測・第 2 報

概要

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To investigate the supersonic flow phenomena related to internal and external flows of high pressure gas pipeline systems, air breathing engines and space planes, a supersonic wind tunnel (pressure vacuum type, Mach4.0 and 2.0) was designed and constructed in Muroran Institute of Technology. This report describes an experimental study on the shock wave/boundary layer interaction (pseudo shock wave, or PSW) in a rectangular duct, using the supersonic wind tunnel. The PSW was visualized by schlieren photography. Detailed distribution of velocity in the PSW was measured by particle image velocimetry (PIV). Boundary layer separation after the first shock wave of the PSW occurred more severely on one of the upper and lower walls than on the other, producing an asymmetric flow field. Deceleration of the core flow around the centerline of the duct was small.
社団法人日本機械学会の論文
2002-10-05