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加强高超声速激波/边界层干扰研究是飞行器研制中一个非常重要的问题。通过解决高超声速试验流场激光散射光信号微弱的问题、流场示踪粒子与试验主气流均匀混合等问题,成功地将基于纳米粒子的平面激光散射技术运用于高超声速激波/边界层干扰研究。作为引导性试验,在高超声速低密度风洞中,在马赫数为5Ma、前室总压为1.0×105Pa的试验条件下,对压缩拐角模型与钝锥模型进行了试验,获得了这两种模型绕流流场图像。随后,在前述试验条件下,对高超声速斜激波与平板边界层相互作用引起的边界层转捩流场结构进行了研究,获得了转捩位置、滑移线及湍流演变过程,表明基于纳米粒子的平面激光散射技术在高超声速边界层流场结构研究方面具有较好的应用前景。此外,还开展了马赫数为10Ma的试验研究,分析了存在的问题与下一步解决措施。
Strengthening the study of hypersonic shock / boundary layer interference is a very important issue in aircraft development. By solving the problem of weak laser light scattering signal in the hypersonic test flow field and the uniform mixing of the flow field tracer particles with the experimental main air flow, the nanoparticle-based planar laser scattering technique is successfully applied to the hypersonic shock / boundary layer interference the study. As a pilot test, the compression corner model and the blunt cone model were tested in a hypersonic low-density wind tunnel under the conditions of a Mach number of 5Ma and a total chamber pressure of 1.0 × 10 5 Pa. Model flow around the flow field image. Subsequently, under the above experimental conditions, the structure of the boundary layer transition caused by the interaction between the hypersonic oblique shock and the slab boundary layer was studied, and the transition position, slip line and turbulent evolution were obtained. Particle planar laser scattering technology has a good application prospect in the field of hypersonic boundary layer flow field structure research. In addition, a pilot study with a Mach number of 10Ma was conducted, analyzing existing problems and solutions for the next step.