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| 概要 |
An X type pseudo-shock wave oscillation in a supersonic diffuser is experimentally investigated by flow visualization using a schlieren method and by static pressure measurements both on the duct cent...er line and on the wall surface. The Mach number just upstream of the pseudo-shock wave is 2.09 which has sufficient magnitude to induce flow separation. The pressure signals are statistically analyzed to obtain root-mean square value, cross correlation coefficient etc. The result shows that there are downstream convected pressure disturbances, of which velocity is about l16m/s in the present experiment. These pressure disturbances explain the oscillation mechanism of the pseudo-shock wave.続きを見る
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