Three-dimensional boundary-layer transition on a cone at Mach 3.5
Three-dimensional boundary-layer transition on a cone at Mach 3.5
复制标题
DOI：
10.1007/bf00209502
复制
发表时间：
1992
影响因子：
2.4
通讯作者：
R. King
中科院分区：
文献类型：
--
作者：
R. King
在马赫数3.5时，对不同迎角下的尖锐5°半锥进行了边界层转捩研究。过渡数据，并没有显着降低自由落体声干扰水平。对于高噪声级数据，观察到了分别在有攻角的锥体的迎风和背风射线上的转捩前缘的向下游和向上游的渐进运动，这与在常规（“噪声”）风洞中获得的数据趋势一致。然而，在本研究中，对于低噪声水平数据，未观察到相同程度的下游移动。过渡被认为是横流为主的被认为是不太容易接受的自由振动声干扰比第一模式（Tollmien-Schlichting）为主的过渡。先前开发的横流转捩雷诺数准则，χtr，max <$200，被认为是不适合当前的情况。提出了一种改进的准则，它包括压缩性和流动几何效应。
A boundary-layer transition study on a sharp, 5° half-angle cone at various angles of attack was conducted at Mach 3.5. Transition data were obtained with and without significantly reduced freestream acoustic disturbance levels. A progressive downstream and upstream motion of the transition front on the windward and leeward rays, respectively, of the cone with angle of attack was observed for the high noise level data in agreement with data trends obtained in conventional (“noisy”) wind tunnels. However, the downstream movement was not observed to the same degree for the low noise level data in the present study. Transition believed to be crossflow dominated was found to be less receptive to freestream acoustic disturbances than first-mode (Tollmien-Schlichting) dominated transition. The previously-developed crossflow transition Reynolds number criterion,χtr,max≈200, was found to be inadequate for the current case. An improved criterion is offered, which includes compressibility and flow-geometry effects.