Abstract
Heat flux measurement in a hypersonic wind tunnel is one of indispensable requirements for designing the next generation re-entry vehicle. Heat flux is usually calculated from a temporal change in temperature on the model surface. Temperature-Sensitive Paint (TSP) is a global temperature measurement technique based on photochemical reaction. In this study, TSP technique was applied to a hypersonic shock tunnel test and the measurement accuracy was investigated with a different TSP thickness. From that result, the optimum thickness of TSP was found to be 0.2μm. Then, the heat flux distribution of a blunt-nosed body with an aerospike was investigated by an optimized TSP thickness
