Abstract
This paper describes the visualization for unsteady fluid phenomena occurring on shock-tube wall by means of Temperature-Sensitive-Paints (TSP). TSP measurement used in this research has been developed for heat-flux estimation in hypersonic shock tunnels which have a few milliseconds test duration, thus TSP has to measure temperature in a few hundred kHz of sampling frequency for highly-accurate heat-flux estimation. Results measured by TSP show a detailed flow structure on the wall, where temperature/heat-flux variations by the incident/reflected shocks, the laminar to turbulent boundary-layer transition, the streak in turbulent boundary-layer, the shock/boundary-layer interaction and the interference between the reflected shock and the contact surface, are clearly visualized and accurately quantified.
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