Abstract
Starting characteristics of a supersonic flow are investigated experimentally in the low Reynolds number range of interest for supersonic flow chemical oxygen-iodine lasers. It is shown that the supersonic flow cannot be started in the test section of constant cross-sectional area at low Reynolds number due to the unacceptale pressure loss, even though a second throat is not utilized. The supersonic flow can be stared at higher Reynolds number with a reasonable pressure ratio which is predicted by the normal shock theory. However, the Mach number in the test section decreases rapidly along the flow due to the presence of thick boundary layers. The use of the diverging test section resuls in a lower critical Reynolds number for starting the supersonic flow and lowers the temperature, although a considerably high pressure ratio is required.
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