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| Abstract |
The interaction between a weak normal shock wave and a turbulent boundary layer at free-stream Mach numbers of 1.14 to 1.62 in a nozzle has been investigated using both a blowdown wind tunnel and an i...ndraft wind tunnel． The flow field has been observed by a schlieren optical method and by pressure measurements at the nozzle centerline. The results show for the first time that even in nozzle flows, post-shock expansion phenomena occur, which were observed experimentally in previous studies on external flows, such as along curved walls of transonic airfoils. The strength of the post-shock expansion increases with the Mach number just up-stream of the shock wave, and this fact suggests the mechanism of generation of a pseudo-shock wave in duct flows．show more
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