<div class="description">
<dl><dd>Thesis advisor: Shreeve, Raymond P</dd>
<dd>"June 2000."</dd>
<dd>Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, June 2000</dd>
<dd>Includes bibliographical references (p. 71)</dd>
<dd>In order to obtain quantitative surface pressure measurements of a transonic compressor rotor using pressure sensitive paint (PSP), the temperature dependence of the paint must be taken into consideration. In the present study, a calibration chamber was built and instrumented such that pressure and temperature could be controlled independently. Photodiodes were used to measure the intensity of light emitted by the PSP. An acquisition program was developed to record the necessary calibration data to obtain an analytical representation of the luminescent response of the pressure-sensitive paint over a range of pressures and temperatures characteristic of transonic fans</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:9116 8/24/00</dd></dl><br>Subjects:</div>
<div class="fn value">
Muller, Judith A.</div>
Internet Archive identifier