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首页> 外文期刊>Journal of visualization >Topological modifications due to ramped vanes in a flare-induced shock-boundary layer interaction flowfleld
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Topological modifications due to ramped vanes in a flare-induced shock-boundary layer interaction flowfleld

机译：爆发引起的冲击边界层相互作用流量升高的叶片导致的拓扑修改

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摘要

Effect of 'ramped vane'-type vortex generators on a shock-induced flow separation in the vicinity of an axisymmetric compression corner was evaluated. Numerical simulations were performed at Mach 2 on a cone-cylinder-flare model with a flare angle of 24°. The undisturbed boundary layer thickness (δ) at the location of the compression corner was 5 mm. A single array of these vortex generators with a device height of 0.28(5 (1.4 mm) was placed on the cylinder surface at different streamwise positions, viz. 5δ, 10δ and 15δ upstream of the compression corner, and their ability to manipulate the shock-boundary layer interaction flowfield was compared. The presence of these devices caused substantial changes in the interaction region and the separation bubble structure. The separation bubble transformed into a series of spade-shaped structures with pockets of attached flow in between them. The ramped vanes increased the separation length along the device centreline, but this effect was attenuated considerably, by bringing them closer to the interaction region. Moving the ramped vanes closer also had a collapsing effect on the spade-shaped structures, which simultaneously widened the attached flow zones in between them.
机译：'倾斜叶片型涡流发生器对轴对称压缩拐角附近的冲击诱导的流动分离的影响。在锥形缸 - 闪光模型上以24°的锥形圆柱形模型在马赫2上进行数值模拟。压缩拐角位置处的未受干扰的边界层厚度（δ）为5mm。在不同流动位置的气缸表面上放置一个设备高度为0.28（5个（1.4毫米）（5（1.4毫米）（5（1.4毫米）的涡流发生器阵列。压缩拐角上游5δ，10δ和15δ，以及它们操纵震动的能力 - 比赛层相互作用流场进行了比较。这些装置的存在在相互作用区域和分离气泡结构中引起了显着的变化。分离气泡转变为一系列铲形结构，在它们之间具有连接流的袋。斜坡叶片沿着装置中心线增加分离长度，但是通过使它们更靠近相互作用区域，显着衰减这种效果。移动斜坡较近的叶片对铲形结构也具有折叠效果，同时加宽了附带的流量区域它们之间。

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  • 来源
    《Journal of visualization》 |2021年第5期|991-1010|共20页
  • 作者

    T. Nilavarasan; G. N. Joshi; A. Misra; C. Manisankar; S. B. Verma;

  • 作者单位

    Department of Aerospace Engineering Defence Institute of Advanced Technology Pune 411025 India;

    Department of Aerospace Engineering Defence Institute of Advanced Technology Pune 411025 India;

    Department of Aerospace Engineering Defence Institute of Advanced Technology Pune 411025 India;

    Experimental Aerodynamics Division National Aerospace Laboratories Bengaluru Karnataka 560017 India;

    Experimental Aerodynamics Division National Aerospace Laboratories Bengaluru Karnataka 560017 India;

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  • 原文格式 PDF
  • 正文语种 eng
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  • 关键词

    Compression corner; Flare; Flow control; Vortex generators; Flow separation;

    机译：压缩角;耀斑;流量控制;涡流发电机;流动分离;

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