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Investigation of Cavity Flow Using Fast-Response Pressure Sensitive Paint

Flaherty, W. and Reedy, Todd M. and Elliott, Gregory S. and Austin, J. M. and Schmit, Ryan F. and Crafton, J. (2013) Investigation of Cavity Flow Using Fast-Response Pressure Sensitive Paint. In: 51st AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition 2013. AIAA , Red Hook, NY. ISBN 9781627481946.

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An experimental study was conducted to investigate the pressure fluctuations on the entire side wall of a rectangular cavity with an L/D of 5.67 using fast-response pressure sensitive paint. Additionally, the performance of four different passive flow-control devices was quantified. Experiments were conducted in the Trisonic Gasdynamics Facility at the Air Force Research Laboratory at Mach 0.7 and 1.5. The frequency spectrum (including Rossiter tones) and sound pressure levels (SPLs) obtained from the pressure sensitive paint (PSP) measurements are validated against data taken with conventional dynamic pressure sensors. The complex flow phenomena over the cavity wall were visualized, and full wall pressure spectra were calculated. The rod in cross flow showed the best peak suppression, followed closely by the flat spoiler. The large triangular step showed some peak suppression, while the ridges did not suppress the peaks at all. High resolution measurements of pressure fluctuations on the wall allowed for the visualization of SPL distribution over the entire cavity wall. This revealed a strong dependence between the Rossiter tone modes and the spatial distribution of SPL that was not possible to resolve with discrete pressure transducers.

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Additional Information:© 2013 by William Flaherty. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. AIAA 2013-0678. The authors would like to thank the Air Force Research Laboratories for supporting this research as part of a Phase II SBIR program with Ryan Schmit and Heidi Wilken as technical monitors. Any opinions, findings, and conclusions or recommendations expressed in this material are those of the authors and do not necessarily reflect the views of AFRL. Additionally, we would like to thank the facility personnel at the TGF. Approved for public release; distribution is unlimited; Case Number 88ABW-2012-6449.
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Air Force Research LaboratoriesUNSPECIFIED
Record Number:CaltechAUTHORS:20140926-151438811
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:50077
Deposited By: Tony Diaz
Deposited On:29 Sep 2014 18:01
Last Modified:03 Oct 2019 07:20

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