<div class="description">
<dl><dd>Thesis advisor(s): Brophy, Christopher</dd>
<dd>"June 2000."</dd>
<dd>Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, June 2000</dd>
<dd>Includes bibliographical references (p. 103)</dd>
<dd>Current interest in developing a low cost, less complex tactical missile propulsion system that operates on readily available liquid fuels and can operate from low subsonic to a flight Mach number of 5 is driving research on pulse detonation engines. This research program involved the design, construction, and testing of a valveless Pulse Detonation Engine using a JP-10/ air mixture as the primary combustible reactants. A small JP-10/oxygen pre- detonation tube was used to initiate the detonation in the JP-10/air mixture in the engine. The engine was tested at various inlet conditions and equivalence ratios in order to determine the detonable regime of the fuel/air mixture. The original area transition from the pre-detonation tube to the main combustion tube appeared to be too extreme, so a tube was added to extend the pre- detonation tube into the throat of a shock focusing device inserted flush with the head end of the main combustion tube to promote more favorable transition conditions</dd>
<dd>Mode of access: World Wide Web</dd>
<dd>System requirements: Adobe Acrobat reader</dd>
<dd>US Navy (USN) author</dd>
<dd>updated dlb 11/2/06</dd></dl><br>Subjects:</div>
<div class="fn value">
Johnson, Robert G.</div>
Internet Archive identifier