Thermal Boundary Layer Effects on Mass Sampling from a Shock Tube
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概要
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The time-of-flight method was applied to the study of thermal boundary layer effects on the sampled gas in a shock-tube mass-sampling system. The effective stangnation temperatures measured by this method agree well with those calculated on the basis of a simple gas-dynamic model for orifice flow through a developing thermal boundary layer in a stagnation Reynolds number range larger than 400, The effect of change in the stagnation temperature on the density of the sample gas was also examined, and the observed density was found to be consistent with the time history of the measured effective stagnation temperature.
- 社団法人応用物理学会の論文
- 1984-01-20
著者
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Teshima Koji
Department Of Aeronautical Engineering Faculty Of Engineering Kyoto University
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Takahashi Norio
Department Of Aeronautical Engineering Faculty Of Engineering Kyoto University
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Deguchi Motoaki
Department Of Aeronautical Engineering Faculty Of Engineering Kyoto University:(present Address)engi
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