Effect of temperature-sensitive-paint thickness on global heat transfer measurement in hypersonic flow
Effect of temperature-sensitive-paint thickness on global heat transfer measurement in hypersonic flow
复制标题
DOI：
10.2514/1.34152
复制
发表时间：
2008-07-01
影响因子：
2.1
通讯作者：
Nakakita, K.
中科院分区：
文献类型：
--
作者：
Nagai, H.;Ohmi, S.;Nakakita, K.
高超音速风洞中的热通量测量是设计下一代再入飞行器的必要要求之一。热通量通常根据模型表面温度的时间变化来计算。温敏涂料提供了一种基于光化学反应的全局温度测量技术。该技术应用于高超声速激波风洞试验，但由于温敏涂料层的厚度带来了不确定性。在本研究中，研究了热敏涂料层厚度与热通量测量精度之间的关系。这些模型在日本宇宙航空研究开发机构的 0.44 米高超音速激波风洞中以 10 马赫的速度进行了测试，并测量了模型表面气动加热引起的热通量。温敏涂料数据与传统热电偶数据的比较表明，测量误差随着涂料层厚度的变化而变化。然后测试了三维机翼-机身模型，以证明优化厚度的温敏涂料的有效性，并观察到由冲击波/冲击波相互作用引起的复杂热通量模式。
Heat flux measurement in a hypersonic wind tunnel is one of the necessary requirements for designing the next-generation reentry vehicle. Heat flux is usually calculated from a temporal change in temperature on a model surface. Temperature-sensitive paint provides a global temperature measurement technique based on photochemical reaction. This technique was applied to a hypersonic shock tunnel test, but there were uncertainties caused by the thickness of the temperature-sensitive-paint layer. In this study, the relationship between the temperature-sensitive-paint layer thickness and the measurement accuracy of heat flux was investigated. The models were tested at Mach 10 in the Japan Aerospace Exploration Agency's 0.44-m hypersonic shock tunnel and the heat flux, caused by aerodynamic heating on the model surface, was measured. A comparison between temperature-sensitive-paint data and conventional thermocouple data showed that the measurement error changed with the paint layer thickness. Then a three-dimensional wing-body model was tested to demonstrate the validity of temperature-sensitive paint of an optimized thickness, and a complicated heat flux pattern caused by the shock wave/shock-wave interaction was observed.