The analysis of the aerodynamic environment of the re-entry vehicle attaches great importance to the design of the novel drag reduction strategies, and the combinational spike and jet concept has shown promising application for the drag reduction in supersonic flows. In this paper, the drag force reduction mechanism induced by the combinational spike and lateral jet concept with the freestream Mach number being 5.9332 has been investigated numerically by means of the two-dimensional axisymmetric Navier-Stokes equations coupled with the shear stress transport (SST) k-ω turbulence model, and the effects of the lateral jet location and its number on the drag reduction of the blunt body have been evaluated. The obtained results show that the drag force of the blunt body can be reduced more profoundly when employing the dual lateral jets, and its maximum percentage is 38.81%, with the locations of the first and second lateral jets arranged suitably. The interaction between the leading shock wave and the first lateral jet has a great impact on the drag force reduction. The drag force reduction is more evident when the interaction is stronger. Due to the inclusion of the lateral jet, the pressure intensity at the reattachment point of the blunt body decreases sharply, as well as the temperature near the walls of the spike and the blunt body, and this implies that the multi-lateral jet is beneficial for the drag reduction.

中文翻译：

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横向射流位置及其数量对超音速流动中钝体减阻的影响

再入飞行器气动环境分析非常重视新型减阻策略的设计，尖峰喷流组合概念在超音速流减阻中显示出广阔的应用前景。本文利用二维轴对称 Navier-Stokes 方程和剪切应力传递 (SST) 对自由流马赫数为 5.9332 的组合尖峰和横向射流概念引起的阻力减小机制进行了数值研究。评价了k-ω湍流模型，以及侧向射流位置及其数量对钝体减阻的影响。所得结果表明，采用双侧射流时，钝体阻力可以更显着地降低，其最大百分比为38.81%，第一、第二侧射流位置布置合理。前导激波与第一侧射流的相互作用对阻力减小有很大影响。当相互作用更强时，阻力减小更明显。由于横向射流的包含，钝体再附着点的压力强度急剧下降，尖刺和钝体壁附近的温度也急剧下降，这意味着多横向射流是有利的用于减阻。当相互作用更强时，阻力减小更明显。由于横向射流的包含，钝体再附着点的压力强度急剧下降，尖刺和钝体壁附近的温度也急剧下降，这意味着多横向射流是有利的用于减阻。当相互作用更强时，阻力减小更明显。由于横向射流的包含，钝体再附着点的压力强度急剧下降，尖刺和钝体壁附近的温度也急剧下降，这意味着多横向射流是有利的用于减阻。