Small Perturbation Theory for Shock‐Tube Attenuation and Nonuniformity
Small Perturbation Theory for Shock‐Tube Attenuation and Nonuniformity
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激波管衰减和不均匀性的小扰动理论
DOI：
10.1063/1.1711363
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发表时间：
1964
影响因子：
4.6
通讯作者：
J. F. Mullen
中科院分区：
文献类型：
--
作者：
H. Mirels;J. F. Mullen
基于自相似的概念，导出了用于计算由于壁面边界层引起的激波管流动微小扰动的封闭形式的表达式。假设理想的横隔膜破裂。在边界层完全为层流或完全湍流的假设下，得到了驱动气体中边界层引起的扰动的广泛的数值结果。被驱动的气体被认为是空气。考虑了各种驱动气体。在激波马赫数达20的情况下，得到了衰减的结果。结果表明，在大的隔板压比下，驱动气体边界层对驱动气体中的扰动的影响很小。结果表明，对于给定的激波马赫数，具有有效驱动的激波管，例如氦，应该比低效驱动的空气具有更小的衰减。后者的结果与已有的实验数据不符。这一差异的来源尚不清楚。
Closed form expressions are derived, based on the concept of self similarity, for evaluating small perturbations of shock tube flow due to the wall boundary layer. Ideal diaphragm rupture is assumed. Extensive numerical results are obtained for the perturbations induced by the boundary layer in the driven gas, assuming that the boundary layer is wholly laminar or wholly turbulent. The driven gas is taken to be air. Various driver gases are considered. Attenuation results are obtained for shock Mach numbers up to 20. It is shown that the effect of the driver gas boundary layer on perturbations in the driven gas is small for large diaphragm pressure ratios. The results indicate that a shock tube with an efficient driver, e.g., helium, should have less attenuation for a given shock Mach number than would an inefficient driver, e.g., air. The latter result disagrees with existing experimental data. The source of the discrepancy is not known.