<div class="description">
<dl><dd>Thesis advisor(s): Raymond P. Shreeve</dd>
<dd>"March 1996."</dd>
<dd>Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1996</dd>
<dd>Includes bibliographical references</dd>
<dd>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</dd>
<dd>Mode of access: World Wide Web</dd>
<dd>System requirements: Adobe Acrobat Reader</dd>
<dd>US Navy (USN) author</dd>
<dd>dk/dk cc:9996 11/8/96</dd></dl><br>Subjects:</div>
<div class="fn value">
Seivwright, Douglas L.</div>
Internet Archive identifier