NASA NTRS · 20030062180
Pulse Detonation Rocket Engine Research at NASA Marshall
Abstract
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 an optimized, fixed PDRE nozzle configuration is reported. The results are compared to a steady-state rocket system using similar modeling assumptions.
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Morris, Christopher I.. 2003-05-09. Pulse Detonation Rocket Engine Research at NASA Marshall. https://ntrs.nasa.gov/citations/20030062180
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