caa a22 4500 606197133 CHVBK 20210128100927.0 cr unu---uuuuu 210128e20150101xx s 000 0 eng 10.1007/s00348-014-1853-y doi (NATIONALLICENCE)springer-10.1007/s00348-014-1853-y Fast-response temperature-sensitive-paint measurements on a hypersonic transition cone [Elektronische Daten] [H. Ozawa, S. Laurence, J. Schramm, A. Wagner, K. Hannemann] 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 40K 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 highunit 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. Springer-Verlag Berlin Heidelberg, 2014 Ozawa H. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut Laurence S. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut Schramm J. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut Wagner A. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut Hannemann K. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut Experiments in Fluids Springer Berlin Heidelberg 56/1(2015-01-01), 1-13 0723-4864 56:1<1 2015 56 348 https://doi.org/10.1007/s00348-014-1853-y text/html Onlinezugriff via DOI BK010053 XK010053 XK010000 Metadata rights reserved Springer special CC-BY-NC licence nationallicence 1 research-article jats NATIONALLICENCE NATIONALLICENCE NL-springer NATIONALLICENCE 856 40 https://doi.org/10.1007/s00348-014-1853-y text/html Onlinezugriff via DOI NATIONALLICENCE 700 1- Ozawa H. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut NATIONALLICENCE 700 1- Laurence S. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut NATIONALLICENCE 700 1- Schramm J. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut NATIONALLICENCE 700 1- Wagner A. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut NATIONALLICENCE 700 1- Hannemann K. Spacecraft Department, Institute of Aerodynamics and Flow Technology, German Aerospace Center, Bunsenstr. 10, 37073, Göttingen, Germany aut NATIONALLICENCE 773 0- Experiments in Fluids Springer Berlin Heidelberg 56/1(2015-01-01), 1-13 0723-4864 56:1<1 2015 56 348