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Role of Air-Breathing Pulse Detonation Engines in High Speed PropulsionIn this paper, the effect of flight Mach number on the relative performance of pulse detonation engines and gas turbine engines is investigated. The effect of ram and mechanical compression on combustion inlet temperature and the subsequent sensible heat release is determined. Comparison of specific thrust, fuel consumption and impulse for the two engines show the relative benefits over the Mach number range.
Document ID
20020009025
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Povinelli, Louis A. (NASA Glenn Research Center Cleveland, OH United States)
Lee, Jin-Ho (NASA Glenn Research Center Cleveland, OH United States)
Anderberg, Michael O. (Massachusetts Inst. of Tech. Cambridge, MA United States)
Date Acquired
September 7, 2013
Publication Date
September 1, 2001
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2001-211163
NAS 1.15:211163
E-13021
IAF-01-S.5.01
Report Number: NASA/TM-2001-211163
Report Number: NAS 1.15:211163
Report Number: E-13021
Report Number: IAF-01-S.5.01
Meeting Information
Meeting: 52nd International Astronautical Congress
Location: Toulouse
Country: France
Start Date: October 1, 2001
End Date: October 5, 2001
Sponsors: French Academy of Sciences, Air and Space National Academy, International Astronautical Federation, Art and Literature Academy, Floral World Academy
Funding Number(s)
PROJECT: RTOP 706-31-23
Distribution Limits
Public
Copyright
Public Use Permitted.

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