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Quasi 1-D Study of Pulse Detonation Rocket Engine Blowdown Gasdynamics and PerformancePulse detonation rocket engines (PDREs) offer potential performance improvements over conventional designs, but represent a challenging modeling task. A quasi 1-D, finite-rate chemistry CFD model for a PDRE is described and implemented. A parametric study of the effect of blowdown pressure ratio on the performance of several different PDRE nozzle configurations is reported.
Document ID
20030062093
Acquisition Source
Marshall Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
Morris, Christopher I. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 21, 2013
Publication Date
December 2, 2002
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: Propulsion Engineering Research Center 14th Annual Symposium on Propulsion
Location: State College, PA
Country: United States
Start Date: December 10, 2002
End Date: December 11, 2002
Sponsors: Pennsylvania State Univ.
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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