Application of fast pressure sensitive paint in hypervelocity flow

W. Flaherty, J. Crafton, G. S. Elliott, J. M. Austin

Research output: Contribution to conferencePaper

Abstract

The development of fast responding pressure sensitive paints for measurements in high-enthalpy, hypersonic flows is reported. Data are obtained for at plate boundary layers in an impulse facility with typical test gas times on the order of hundreds of microseconds. The fast pressure sensitive paint is found to have the required response time and sufficient signal level to visualize vortical boundary layer structures in a Mach 5.12 freestream. The flow behind protuberance strips with different geometries is evaluated with measurements of the vortex frequency and diameter, as well as breakdown distance. Comparisons with static pressure measurements made using pressure taps show differences of up to a factor of three, and calibration sources as well as an alternative lifetime measurement method remain to be investigated.

Original languageEnglish (US)
DOIs
StatePublished - 2011
Event49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition - Orlando, FL, United States
Duration: Jan 4 2011Jan 7 2011

Other

Other49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
CountryUnited States
CityOrlando, FL
Period1/4/111/7/11

ASJC Scopus subject areas

  • Aerospace Engineering

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    Flaherty, W., Crafton, J., Elliott, G. S., & Austin, J. M. (2011). Application of fast pressure sensitive paint in hypervelocity flow. Paper presented at 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, FL, United States. https://doi.org/10.2514/6.2011-848