近空间飞行器在超/高超声速飞行时，流场中通常都存在流动分离区，流动分离之后物面的载荷分布（气动力、气动加热量等）与附着流相比发生了明显的变化，有明显的峰值区，这些很高的峰值曾导致局部结构破坏；分离流动中的非定常流动特性明显，非定常载荷与噪音不可忽视。. 本项研究继续在前期项目（项目批准号：90816009、91116009）列出的实验条件与实验模型下，开展第三种途径（脉动压力测量）的非定常分离流场特性研究；并结合已完成的三种实验结果进行分析与对比，说明高超声速条件下典型的非定常分离流场中判定物面流动分离的物理现象，多方面测量可为工程应用提供基础。. 本项研究涉及面广，难度高，综合性强，应用需求明确，国内外未见类似的系统研究，研究结果不仅可以进一步阐明流动的非定常物理过程，同时提供可定量的非定常实验数据。

The super/hypersonic flow is attached the surface or separated from the surface on the vehicle, since the load distributions on the vehicle surface are visible different in both two cases of separated flow and attached flow, and some local structure had been broken by peak load, which was exist in separated flow.The unsteady load with air noise could be considered.. This project will research unsteady separated flow by means of the third approach(fluctuating pressure measurement) under the same conditions and models of the previous projects(90816009,91116009).Three types of measurement results will be compared and analyzed to show physical phenomena of flow separation in typical hypersonic unsteady separated flow. Combination results could provide basis for engineering application. . The present study involves a wide range of research contents and is very comprehensive and difficult. Application requirement is clear and no similar system research work had been done at home and abroad. The research results can explain physical process of unsteady flow and provide applicable regular unsteady experimental data.