Abstract
Pulse detonation rocket engines (PDREs) offer potential performance improvements over conventional designs, but represent a challenging modeling task. An axisymmetric, finite-rate chemistry computational fluid dynamics model for PDREs is described and implemented. This model is compared to experimental data from the literature in order to determine its accuracy over a wide range of blowdown pressure ratios. Additionally, multiple-pulse simulations of four different PDRE nozzle geometries are evaluated for three different pressure ratios. The nozzle geometries vary the throat size while holding the expansion ratio constant for each pressure ratio. The results indicate that, at higher pressure ratios, it is possible to obtain a specific impulse matching, or even exceeding, that for single-pulse simulations.
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