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 ( 160 R e t 780 ) to consist of liquid droplets ranging in size from 0.1 to 3.0    μ m 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 35 % possible for sub-micrometer-scale droplets at R e t = 780 and a mass loading of 100%.


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    Title :

    Impact of Dilute Multiphase Flow in Supersonic Micronozzles


    Contributors:

    Published in:

    Publication date :

    2019-01-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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