Application of pressure-sensitive paint in shock-boundary layer interaction experiments
By: Douglas L. Seivwright
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1996
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 184
Description: A new type of pressure transducer, pressure-sensitive paint, was used to obtain pressure distributions associated with shock-boundary layer interaction. Based on the principle of photoluminescence and the process of oxygen quenching, pressure-sensitive paint provides a continous mapping of a pressure field over a surface of interest. The data measurement and acquisition system developed for use with the photoluminescence sensor was evaluated first using an underexpanded jet blowing over a flat plate. Once satisfactory results were obtained, the system was used to examine shock-boundary layer interaction in a blow-down supersonic wind tunnel at Mach numbers of 1.4 and 1.7. Details of the measurement technique, and discussion of the flow fields which were examined, are reported.
Notes: Thesis advisor(s): Raymond P. Shreeve.

"March 1996."

Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1996.

Includes bibliographical references.

Approved for public release; distribution unlimited.

Also available online.

Mode of access: World Wide Web.

System requirements: Adobe Acrobat Reader.

US Navy (USN) author.

dk/dk cc:9996 11/8/96