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Dissociation and Recombination Effects on the Performance of Pulse Detonation EnginesThis paper summarizes major theoretical results for pulse detonation engine performance taking into account real gas chemistry, as well as significant performance differences resulting from the presence of ram and compression heating. An unsteady CFD analysis, as well as a thermodynamic cycle analysis, was conducted in order to determine the actual and the ideal performance for an air-breathing pulse detonation engine (PDE) using either a hydrogen-air or ethylene-air mixture over a flight Mach number range from 0 to 4. The results clearly elucidate the competitive regime of PDE application relative to ramjets and gas turbines.
Document ID
20030102270
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Povinelli, Louis A. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 2003
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2003-212538
Meeting Information
Meeting: 16th International Symposium on Airbreathing Engines
Location: Cleveland, OH
Country: United States
Start Date: August 31, 2003
End Date: September 5, 2003
Sponsors: International Society for Airbreathing Engines
Funding Number(s)
WBS: WBS-22-719-10-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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