The leeside vortex structures on delta wings with sharp leading edges were studied for supersonic flow at the Institute of Theoretical and Applied Mechanics of the Russian Academy of Sciences in Novosibirsk. The experiments were carried out with three wings with sweep angles of chi = 68 degrees, 73 degrees, and 78 degrees and parabolic profiles in the 0.6 x 0.6 m(2) test section of the blow-down wind tunnel T-313 of the institute. The test conditions were varied from Mach numbers M = 2 to 4, unit Reynolds numbers from Re-1 = 26 x 10(6) to 56 x 10(6) m(-1), and angles of attack from x = 0 degrees to 22 degrees. The results of the investigations revealed that for certain flow conditions shocks are formed above, below, and between the primary vortices. The experimental data were accurate enough to detect the onset of secondary and tertiary separation as well as other boundaries. The various flow regimes discussed in the literature were extended in several cases. The major findings are reported. [References: 14]
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机译：在新西伯利亚的俄罗斯科学院理论与应用力学研究所研究了具有尖锐前缘的三角翼上的背风涡结构，以进行超音速流动。实验是在研究所排污风洞T-313的0.6 x 0.6 m（2）测试段中使用三个机翼，其扫掠角为chi = 68度，73度和78度，并且具有抛物线轮廓。测试条件从马赫数M = 2更改为4，单位雷诺数从Re-1 = 26 x 10（6）到56 x 10（6）m（-1），攻角从x = 0度到22度研究结果表明，对于某些流动条件，在初级涡旋的上方，下方和之间形成冲击。实验数据足够准确，可以检测到第二和第三级分离以及其他边界的发生。文献中讨论的各种流动方式在几种情况下得到了扩展。报告了主要发现。 [参考：14]
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