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Airbreathing Pulse Detonation Engine PerformanceThis paper presents performance results for pulse detonation engines (PDE) taking into account the effects of dissociation and recombination. The amount of sensible heat recovered through recombination in the PDE chamber and exhaust process was found to be significant. These results have an impact on the specific thrust, impulse and fuel consumption of the PDE.
Document ID
20020063440
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Povinelli, Louis A.
(NASA Glenn Research Center Cleveland, OH United States)
Yungster, Shaye
(NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
May 1, 2002
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2002-211575
NAS 1.15:211575
ICOMP-2002-02
E-13359
Report Number: NASA/TM-2002-211575
Report Number: NAS 1.15:211575
Report Number: ICOMP-2002-02
Report Number: E-13359
Funding Number(s)
PROJECT: RTOP 706-21-33
Distribution Limits
Public
Copyright
Public Use Permitted.
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