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Control of Shock/Boundary-Layer Interaction for Hypersonic Inlets by Highly Swept Microramps

机译:高扫掠微斜坡控制高超声速进气口的冲击/边界层相互作用

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摘要

The performance of hypersonic inlets is significantly affected by the presence of shock/boundary-layer interactions. To examine the potential of microramps for shock/boundary-layer interaction control in a finite-width duct, a detailed experimental and computational study has been conducted with a separated oblique shock/boundary-layer interaction generated by a 12 deg shock generator at Mach 3.5. Results show that the shock/boundary-layer interaction in the finite-width duct generates complex three-dimensional flow structures with significant swirling nature, and the traditional microramps cannot suppress the separation effectively. Therefore, a type of highly swept microramps with a large chord ratio and small incidence angle is brought forward and investigated. By the precompression effect, the dividing effect, the obstructing effect, and the energizing effect, the highly swept microramps with a height of 0.24 times the boundary-layer thickness show good control capability on the shock/ boundary-layer interaction. In addition, the efficiency of the control method for different shock impingement positions is obtained, indicating that the separation can be well controlled when the shock impinges on the aft part of the highly swept microramps.
机译:冲击/边界层相互作用的存在极大地影响了高超声速进气口的性能。为了检查微斜坡在有限宽度管道中控制冲击/边界层相互作用的潜力,已对由12度冲击发生器在3.5马赫时产生的单独的倾斜冲击/边界层相互作用进行了详细的实验和计算研究。 。结果表明,有限宽管道中的激波/边界层相互作用产生了复杂的三维流动结构,具有明显的旋流特性,而传统的微坡道不能有效地抑制分离。因此,提出并研究了一种弦速比大,入射角小的高扫频微斜坡。通过预压缩效果,划分效果,阻碍效果和激励效果,高度为边界层厚度的0.24倍的高扫掠微坡道对冲击/边界层相互作用具有良好的控制能力。另外,获得了针对不同冲击撞击位置的控制方法的效率,表明当冲击撞击在高度扫掠的微型斜坡的后部时,可以很好地控制分离。

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  • 来源
    《Journal of propulsion and power》 |2015年第1期|133-143|共11页
  • 作者单位

    Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Collaborative Innovation Center of Advanced Aero-Engine, 210016 Nanjing, People's Republic of China;

    Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Collaborative Innovation Center of Advanced Aero-Engine, 210016 Nanjing, People's Republic of China;

    Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Collaborative Innovation Center of Advanced Aero-Engine, 210016 Nanjing, People's Republic of China;

    Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Collaborative Innovation Center of Advanced Aero-Engine, 210016 Nanjing, People's Republic of China;

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