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 & 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.
Quasi-One-Dimensional Modeling of Pulse Detonation Rocket Engines
39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit ; 2003 ; Huntsville, AL, United States
2003-01-01
Preprint
No indication
English
Quasi-One-Dimensional Modeling of Pulse Detonation Rocket Engines
British Library Conference Proceedings | 2003
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