In this study, a computational investigation of multiphase flow within supersonic micronozzles has been performed in an effort to quantify the impact on thrust production and nozzle efficiency. Motivated by a scenario of incomplete chemical decomposition within a miniaturized, microfabricated monopropellant micropropulsion system, the multiphase flow is modeled over a range of throat Reynolds numbers to consist of liquid droplets ranging in size from 0.1 to in diameter (Stokes numbers 0.01–10.0) and with mass loadings up to 100% relative to the gas phase. The results indicate that the presence of liquid droplets within the supersonic gas flow can substantially degrade micronozzle performance with thrust reductions approaching 19% and specific impulse reductions of up to possible for sub-micrometer-scale droplets at and a mass loading of 100%.
Impact of Dilute Multiphase Flow in Supersonic Micronozzles
Journal of Spacecraft and Rockets ; 56 , 1 ; 190-199
2019-01-01
Conference paper , Article (Journal)
Electronic Resource
English
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