Pulse 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.
Quasi 1-D Study of Pulse Detonation Rocket Engine Blowdown Gasdynamics and Performance
Propulsion Engineering Research Center 14th Annual Symposium on Propulsion ; 2002 ; State College, PA, United States
02.12.2002
Preprint
Keine Angabe
Englisch
Simplified Analysis of Pulse Detonation Rocket Engine Blowdown Gasdynamics and Performance
British Library Conference Proceedings | 2002
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