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Pulse Detonation Rocket Engine Research at NASA MarshallPulse 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 an optimized, fixed PDRE nozzle configuration is reported. The results are compared to a steady-state rocket system using similar modeling assumptions.
Document ID
20030062180
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
September 7, 2013
Publication Date
May 9, 2003
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: 16th ONR Propulsion Meeting
Location: Los Angeles, CA
Country: United States
Start Date: June 9, 2003
End Date: June 11, 2003
Sponsors: Office of Naval Research
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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