Abstract
A quantitative global intensity-based temperature-sensitive paint heat transfer measurement system has been developed at Arnold Engineering Development Center Hypervelocity Wind Tunnel No. 9. The system has been designed for use with metal wind-tunnel models in long-duration (on the order of seconds) hypersonic flows. A numerical finite differencing scheme has been proposed for calculating convective heat flux from the paint's surface emission intensity data. As part of the development effort, surface emission intensity data have been collected on a model of a NASA Orion Crew Exploration Vehicle capsule in Mach 10 flow. The proposed data reduction algorithm has been applied to generate high-resolution quantitative heat transfer maps of the model's heat shield. Good quantitative agreement has been achieved between the heat transfer maps and the baseline conventional instrumentation data on the majority of the heat shield surface.
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