Application of Fast Pressure Sensitive Paint in Hypervelocity Flow
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.
Additional Information
© 2011 by University of Illinois. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. AIAA 2011-848. This work was supported in part by the Air Force Research Laboratory through award FA8650-10-M-3023 with Dr. Daniel Tejtel as Program Manager and in part by the Air Force Office of Scientific Research through award FA9550-08-1-0172 with Dr. John Schmisseur as Program Manager.Attached Files
Published - 385397.pdf
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Additional details
- Eprint ID
- 50093
- Resolver ID
- CaltechAUTHORS:20140929-111458194
- Air Force Research Laboratory
- FA8650-10-M-3023
- Air Force Office of Scientific Research (AFOSR)
- FA9550-08-1-0172
- Created
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2014-09-29Created from EPrint's datestamp field
- Updated
-
2021-11-10Created from EPrint's last_modified field
- Caltech groups
- GALCIT