Smooth leading edge transition in hypersonic flow

Smooth leading edge transition in hypersonic flow
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高超声速流中的平滑前缘过渡

DOI：
10.1007/s003480050276
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发表时间：
1999
期刊：
影响因子：
--
通讯作者：
T. A. Roquefort
T. A. Roquefort
中科院分区：
--
文献类型：
--
作者：
L. Gaillard;E. Bénard;T. A. Roquefort

文献摘要

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在下吹式风洞中研究了高超声速绕流中光滑后掠圆柱附接线的边界层沿着转捩。借助于不同的模型，在不同的后掠角（60°？什么？80°）。通过热通量测量间接检测过渡。通过液氮冷却模型，研究了壁温与滞流温度比的影响。
The boundary layer transition along the attachment line of a smooth swept circular cylinder in hypersonic flow is investigated in a blowdown wind tunnel. A wide range of spanwise Mach numbersMe(3.28 to 6.78) is covered with the help of different models at several sweep angles (60°?Λ?80°). The transition is indirectly detected by means of heat flux measurements. The influence of the wall to stagnation temperature ratio is investigated by cooling the model with liquid nitrogen.