Abstract
This paper describes an experimental study on the supersonic internal flows with Pseudo-Shock Waves (PSW) in a straight square duct with cross section of 80×80mm^2, using the pressure-vacuum type Mach 4 and Mach 2 supersonic wind tunnel of Muroran Institute of Technology. The free stream Mach number and unit Reynolds number just upstream of the PSW were M_∞=3.98, R_∞=2.22×10^7m^<-1> and M_∞=1.96, R_∞=2.43×10^7m^<-1>. The oscillation phenomena of Mach 4 and Mach 2 PSW were clarified by high speed digital camera observation and duct wall pressure fluctuation measurements.
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