An LDA investigation of the normal shock wave boundary layer interaction
An LDA investigation of the normal shock wave boundary layer interaction
复制标题
法向激波边界层相互作用的 LDA 研究
DOI：
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发表时间：
1990
期刊：
影响因子：
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通讯作者：
T. Keith
中科院分区：
文献类型：
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作者：
R. M. Chriss;W. Hingst;A. Strazisar;T. Keith
对两种正激波-边界层干扰进行了非侵入性测量。在整个相互作用区域进行了二维测量，而在冲击波附近进行了三维测量。这些测量是在一个连续流超音速风洞的试验段的拐角处进行的，风洞中的正激波已经稳定。LDA、表面压力测量和流动可视化技术用于两种自由流马赫数测试用例：1.6和1.3。前者包含分离的流动区域和激波系统。后者被认为远没有那么复杂。报告的结果详细定义了每种情况下的流场结构。
Nonintrusive measurements have been made of two normal shock wave-boundary layer interactions. Two-dimensional measurements were made throughout the interaction region while three-dimensional measurements were made in the vicinity of the shock wave. The measurements were made in the corner of the test section of a continuous flow supersonic wind tunnel in which a normal shock wave had been stabilized. LDA, surface pressure measurement and flow visualization techniques were employed for two freestream Mach number test cases: 1.6 and 1.3. The former contained separated flow regions and a system of shock waves. The latter was found to be far less complicated. The reported results define the flowfield structure in detail for each case.