论文部分内容阅读
通过采取快速插入、建立同步采集系统等措施,在中国航天空气动力技术研究院FD-07常规高超声速风洞建立了磷光热图技术,并成功地获得了平板三角翼模型表面热流分布.基于实验结果,初步分析了来流Reynolds数等参数对三角翼表面热流分布的影响.结果表明,三角翼外形中心线处转捩靠后,两侧转捩靠前,且随着来流Reynolds数的增加,转捩位置进一步前移.总的来说,磷光热图技术能够直观地显示流动转捩发生的位置以及转捩后湍流区的形状,为高超声速飞行器热防护设计提供了一种新的技术途径.
Through the rapid insertion and the establishment of synchronous acquisition system, the phosphorescence thermography technique was established in the FD-07 conventional hypersonic wind tunnel of China Aerospace Aerodynamics Research Institute and the surface heat flow distribution of the flat delta wing model was successfully obtained.Based on the experiment The results show that the influence of Reynolds number and other parameters on the surface heat flow distribution of the delta wing is analyzed preliminarily.The results show that when the center line of the delta wing revolves backward and the two sides turn forward, and as the Reynolds number increases , The position of the transition further forward.In general, the phosphorescent heat map technology can visually show the location of the flow transition and the shape of turbulence zone after transition, providing a new technology for the hypersonic vehicle thermal protection design way.