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.
Pulse Detonation Rocket Engine Research at NASA Marshall
16th ONR Propulsion Meeting ; 2003 ; Los Angeles, CA, United States
09.05.2003
Preprint
Keine Angabe
Englisch
Pulse Detonation Rocket Engine Research at NASA Marshall
NTRS | 2003
|Pulse Detonation Rocket Engine Research at NASA Marshall
NTIS | 2003
|