中文摘要：

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1．0×10^5Pa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。

英文摘要：

It is very essential to strengthen the study and set up the effective estimate or prediction method of shock wave and boundary layer interactions. These problems of the low scattering signal, the mixing uniformity between the flow tracer and experimental gas were settled so that the study of hypersonic shock - wave/boundary layer inter- actions could be carried out using nano - tracer planar laser scattering technique. Under the experimental condition of Mach number M5, total pressure1. 0 ×10^5Pa,A guidance test on a ramp model and a blunt cone model was in- vestigated and the flow field picture was obtained. Subsequently, at the above - mentioned conditions, the hyper- sonic shock- wave and boundary layer interactions on the flat plate model were experimentally carried out. The transitional position, slip line and evolving process of turbulent flow in boundary layer on the flat model were gained. These results also show that it can play an important role in the hypersonic flow field diagnosis to use nano -tracer planar laser scattering techniques. In addition, the experiment at Mach number M10 was also carried out. Some problems arisen from the experiment and the measures to be taken were analyzed.