Abstract
Experiments are performed using a fast-response temperature-sensitive-paint (TSP) technique to measure the heat-flux distribution on a slender cone in a hypersonic shock tunnel under both laminar and transitional conditions. The millisecond-order test duration together with the self-luminosity of shock layers place stringent conditions on the choice of TSP luminophore and the TSP-layer thickness that can be employed. The luminosity and dimming from particulates in the free-stream cause additional problems in interpreting the obtained intensity profiles. Nevertheless, favorable agreement with thermocouple-based measurements show that it is possible to derive quantitatively accurate heat-flux distributions with the TSP technique for temperature rises of up to approximately 40 K above room temperature. The technique accuracy is adversely affected at higher temperatures, which is thought to result from non-constant thermal properties of the insulating base layer. At high unit Reynolds number conditions, time-resolved heat-flux distributions show large-scale unsteadiness in the boundary-layer transition location and reveal transient streamwise streaks developing in the transitional region.
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Acknowledgments
The authors wish to acknowledge the HEG technical staff, in particular Ingo Schwendtke, Mario Jünemann, and Sarah Trost for assistance in preparing the model and running the tunnel. The advice of the DLR Göttingen PSP group, especially Christian Klein, Walter Beck, and Ulrich Henne, was also invaluable during the development and calibration of the TSP technique. We also wish to thank Bryan Schmidt of Caltech and two anonymous reviewers for useful suggestions.
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Ozawa, H., Laurence, S.J., Schramm, J.M. et al. Fast-response temperature-sensitive-paint measurements on a hypersonic transition cone. Exp Fluids 56, 1853 (2015). https://doi.org/10.1007/s00348-014-1853-y
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DOI: https://doi.org/10.1007/s00348-014-1853-y