Temperature- and pressure-sensitive paint measurements in short-duration hypersonic flow

Surface temperatures and pressures were measured on an elliptic cone liftin g body in a hypersonic flowfield using thin-film (similar to5 mum) temperat ure- and pressure-sensitive paints (TSPs and PSPs), The tests were conducte d in the 48-inch hypersonic shock tunnel (48-inch HST) at Calspan-Universit y of Buffalo Research Center and were part of a more comprehensive experime ntal study examining the three-dimensional characteristics of laminar, tran sitional, and turbulent flow over the model. Measurement opportunity in the 48-inch HST was limited by the short duration of steady freestream conditi ons of the driven gas; image acquisition times were similar to3 ms. Images of the coatings applied to the broad side of the symmetric elliptic cone we re calibrated with in situ static pressure and surface-film temperature mea surements. The TSP results illustrate the higher heat transfer rates and ch ange in boundary-layer transition over the model surface caused by the nose geometry, and the PSP results show a mild pressure gradient over the inter rogated surface region. Submillisecond TSP acquisition using a high-speed i mager demonstrated the feasibility of measuring the surface temperature ris e.