Boundary-Layer Transition on an Axisymmetric Body at Incidence at Mach 1.2
Boundary-Layer Transition on an Axisymmetric Body at Incidence at Mach 1.2
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入射速度为 1.2 马赫时轴对称体上的边界层转变
DOI：
10.2514/1.8719
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发表时间：
2006
期刊：
影响因子：
2.5
通讯作者：
Yoshine Ueda
中科院分区：
文献类型：
--
作者：
H. Sugiura;N. Tokugawa;Yoshine Ueda
对 1 度和 2 度入射角的轴对称鼻子模型上的边界层转变进行了实验研究，速度为 1.2 马赫。该模型的配置是 Sears-Haack 体的前部，定义为具有超音速流中 0 度入射时体积引起的最小波阻。使用红外相机获得表面粗糙度约为 0.1 μ 的过渡位置。应用非稳态压力传感器来研究导致转变的不稳定机制。这些结果表明，最尾部的过渡发生在背风射线上，而不是在尖锥体上观察到的迎风射线上。 Tollmien-Schlichting 不稳定性在迎风射线上的过渡过程中占主导地位，并且横流不稳定性被认为在类似于尖锥上的过渡的一侧上占主导地位。然而，与尖锥体的情况相比，过渡发生在背风射线的更靠后的位置，并且过渡前沿是由由于侧面更靠前的过渡而形成的湍流楔形决定的。在 1 度入射角处观察到被认为是横流行波的扰动，其测量频率与使用可压缩线性 e N 代码计算的最大放大频率非常一致。
Experimental investigation of the boundary-layer transition on an axisymmetric nose model at 1- and 2-deg incidence was conducted at Mach 1.2. The configuration of the model is the forward part of a Sears-Haack body defined to have minimum wave drag caused by volume at 0-deg incidence in supersonic flow. Transition locations were obtained with small surface roughness on the order of 0.1 μ using an infrared camera. An unsteady pressure transducer was applied to investigate instability mechanisms that lead to transition. These results show that the most aft transition occurred on the leeward ray rather than on the windward rays as observed on sharp cones. Tollmien-Schlichting instability dominated the transition process on the windward ray, and crossflow instability was assumed to dominate on the side similar to the transition on the sharp cones. However, transition occurred more aft on the leeward ray than for the case of the sharp cones, and the transition front was determined by turbulent wedges formed as a consequence of the more forward transition on the side. The disturbance believed to be a traveling crossflow wave was observed at 1-deg incidence, and its measured frequency was in good agreement with the maximum amplified frequency, which was calculated using a compressible linear e N code.