Boundary-layer transition on cones at angle of attack in a Mach-6 Quiet Tunnel
Boundary-layer transition on cones at angle of attack in a Mach-6 Quiet Tunnel
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DOI：
10.2514/6.2010-1062
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发表时间：
2010-01
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影响因子：
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通讯作者：
E. Swanson
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文献类型：
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作者：
E. Swanson
在Purdue Boeing/AFOSR马赫数为6的静风洞中，进行了一系列高超声速7°锥头有攻角边界层转捩的实验研究。用温敏漆（TSP）和油流技术观察了锥上的边界层转捩和横流涡。在安静流中，在攻角为6°的尖锥和球形钝锥上观察到层流，而在噪声流中，在锥上观察到向湍流的转变，表明风洞噪声对转变有显著影响。在噪声流中，在6%钝锥上观察到偏航-前转捩前缘。在噪声条件下，在尖锥上的湍流边界层中观察到TSP和油流的横流涡。TSP也被用来观察横流涡在安静的流动。静流中尖锥和6%钝锥上的旋涡与噪声流中尖锥上的旋涡相似。噪声流中偏航尖锥上x = 2英寸（轴向）处间距为9°的粗糙元阵列影响转捩，这显然是由横流不稳定性引起的，正如NASA兰利计算所预测的那样。在静流条件下，粗糙度阵列对流动没有影响。
A series of experiments have been conducted to study hypersonic boundary-layer transition over 7° cones at angle of attack in the Purdue Boeing/AFOSR Mach-6 Quiet Tunnel. The temperature-sensitive-paint (TSP) and oil-flow techniques were used to observe boundarylayer transition and crossflow vortices on the cones. Laminar flow was observed on sharp and spherically-blunt cones at 6° angle-of-attack in quiet flow, while transition to turbulence was observed on the cones in noisy flow, indicating a marked effect of tunnel noise on transition. A yawside-forward transition front was observed on a 6%-blunt cone in noisy flow. Crossflow vortices were observed with both TSP and oil flow under noisy conditions in the turbulent boundary layer on a sharp cone. TSP was also used to observe crossflow vortices in quiet flow. The vortices on both a sharp and a 6%-blunt cone in quiet flow were similar to those seen on the sharp cone in noisy flow. An array of roughness elements at x = 2 inches (axially) with a spacing of 9° on a yawed sharp cone in noisy flow influenced transition that was apparently induced by the crossflow instability, as predicted by NASALangley computations. No influence of the roughness array was observed in quiet flow.