Effect of Microvortex Generators On Seperated Normal Shock/ Boundary Layer Interactions
Effect of Microvortex Generators On Seperated Normal Shock/ Boundary Layer Interactions
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DOI：
10.2514/1.22770
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发表时间：
2007-09
影响因子：
2.2
通讯作者：
H. Holden;H. Babinsky
中科院分区：
文献类型：
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作者：
H. Holden;H. Babinsky
在一个泄放式超音速风洞中进行了实验，研究了在马赫数为1.5、自由雷诺数为28 × 10 - 6时，放置在正激波/湍流边界层干扰上游的亚边界层涡流发生器的影响。基于流入边界层位移厚度的雷诺数为26，000。研究了两种类型的亚边界层涡流发生器：楔形和反向旋转叶片。结果表明，叶片式亚边界层涡发生器消除了激波诱导的分离，而楔形亚边界层涡发生器大大减小了激波诱导的分离。当放置在超音速部分的流动，这两种类型的亚边界层涡流发生器造成的波型组成的冲击，再膨胀，和冲击。再膨胀和双激波是不希望的特征，因为它们等同于增加的总压损失。此外，有迹象表明，正激波/边界层相互作用降低了旋涡强度。总的来说，叶片型亚边界层涡流发生器是更有效的装置，因为它们消除了激波诱导的分离，对激波结构的有害影响最小。
Experiments have been performed in a blowdown supersonic wind tunnel to investigate the effect of subboundary layer vortex generators placed upstream of a normal shock/turbulent boundary layer interaction at a Mach number of 1.5 and a freestream Reynolds number of 28 x 10 6 . The Reynolds number based on the inflow boundary layer displacement thickness was 26,000. Two types of subboundary layer vortex generators were investigated: wedge-shaped and counter-rotating vanes. It was found that the vane-type subboundary layer vortex generators eliminated and the wedge-type subboundary layer vortex generators greatly reduced the shock-induced separation. When placed in the supersonic part of the flow, both types of subboundary layer vortex generators caused a wave pattern consisting of a shock, reexpansion, and shock. The reexpansion and double shocks are undesirable features because they equate to increased total pressure losses. Furthermore there are indications that the vortex intensity is reduced by the normal shock/boundary layer interaction. Overall, the vane-type subboundary layer vortex generators were the more effective devices as they eliminated the shock-induced separation and had the least detrimental effect on the shock structure.