Incipient Separation of a Supersonic, Turbulent Boundary Layer, Including Effects of Heat Transfer
Incipient Separation of a Supersonic, Turbulent Boundary Layer, Including Effects of Heat Transfer
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DOI：
10.2514/3.50245
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发表时间：
1972-01
期刊：
影响因子：
2.5
通讯作者：
F. Spaid;John C. Frishett
中科院分区：
文献类型：
--
作者：
F. Spaid;John C. Frishett
在马赫数为2.9，雷诺数为2.2 ~ 5.9 × 104，壁温与恢复温度之比为1.05 ~ 0.47的条件下，进行了紊流边界层与压缩角干扰的实验研究。绝热壁数据表明，用液线法测定的初始分离角为6.5°。静压分布被认为是不敏感的小区域的分离流的存在。结合其它试验数据，本文的结果表明，初始分离角随雷诺数的增加而增大。壁面冷却的作用是增大初始分离角，减小分离距离。
An experimental study of the interaction of a turbulent boundary layer with a compression corner has been conducted at a Mach number of 2.9, Reynolds number based upon boundary-layer thickness of 2.2 to 5.9 x 104, and ratio of wall-temperat ure-to-recovery-temperature of 1.05 to 0.47. Adiabatic wall data showed an incipient separation angle of 6.5°, as determined by the liquid line method. The static pressure distribution was found to be insensitive to the presence of small regions of separated flow. The present results, combined with other data, shown an increasing trend of incipient separation angle with Reynolds number. The effect of wall cooling was to increase the incipient separation angle and reduce the separation distance.