Abstract

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 0.28δ (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.

Graphic Abstract

中文翻译：

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耀斑引起的激波-边界层相互作用流场中叶片倾斜导致的拓扑变化

摘要

评估了“斜叶片”型涡流发生器对轴对称压缩角附近的激振流动分离的影响。数值模拟是在锥角为24°的圆锥-圆柱-扩口模型上以2马赫数进行的。压缩角的位置处的原状边界层厚度（δ）为5mm。用0.28的装置高度这些涡流发生器的一个单个阵列δ（1.4 MM）在不同的位置流向被放置在圆柱体表面上，即 5 δ，10 δ和15 δ比较了压缩角的上游，以及它们操纵冲击边界层相互作用流场的能力。这些装置的存在引起相互作用区域和分离气泡结构的实质性变化。分离气泡转变为一系列的铲形结构，在它们之间有相连的流动袋。倾斜的叶片增加了沿设备中心线的分离长度，但是通过使它们更靠近相互作用区域，这种效果大大减弱了。将倾斜的叶片移得更近也对铲形结构产生了塌陷的作用，这同时加宽了它们之间的连接流动区域。

图形摘要