Title: Temperature- and Pressure-Sensitive Paint Measurements in Short-Duration
 Hypersonic Flow
 Author(s): J. P. Hubner; B. F. Carroll; K. S. Schanze; H. F. Ji; M. S. Holden
 Source: AIAA Journal      Volume: 39 Number: 4 Page: 654 -- 659
 Publisher: American Institute of Aeronautics and Astronautics
 Abstract: Surface temperatures and pressures were measured on an elliptic cone lifting
 body in a hypersonic flowfield using thin-film ( 5 m) temperature- and pressure-sensitive
 paints (TSPs and PSPs). The tests were conducted in the 48-inch hypersonic shock tunnel
 (48-inch HST) at Calspan-University of Buffalo Research Center and were part of a more
 comprehensive experimental study examining the three-dimensional characteristics of
 laminar, transitional, and turbulent flow over the model. Measurement opportunity in the
 48-inch HST was limited by the short duration of steady freestream conditions of the driven
 gas; image acquisition times were  3 ms. Images of the coatings applied to the broad side
 of the symmetric elliptic cone were calibrated with in situ static pressure and surface-film
 temperature measurements. The TSP results illustrate the higher heat transfer rates and
 change in boundary-layer transition over the model surface caused by the nose geometry,
 and the PSP results show a mild pressure gradient over the interrogated surface region.
 Submillisecond TSP acquisition using a high-speed imager demonstrated the feasibility of
 measuring the surface temperature rise.