Numerical Simulation of Micronozzles with Comparison to Experimental Results

Details Numerical Simulation of Micronozzles with Comparison to Experimental Results Numerical Simulation of Micronozzles with Comparison to Experimental Results

Oct 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.555e.113t&link_type=abstract

Proceedings of the 4th International Spacecraft Propulsion Conference (ESA SP-555). 2-9 June, 2004, Chia Laguna (Cagliari), Sard

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A numerical analysis of conical micronozzle flows has been conducted using the commercial software package CFD-RC FASTRAN [13]. The numerical results have been validated by comparison with direct thrust and mass flow measurements recently performed in ESTEC Propulsion Laboratory on Polyflex Space Ltd. 10mN Cold-Gas thrusters in the frame of ESA CryoSat mission. The flow is viscous dominated, with a throat Reynolds number of 5000, and the relatively large length of the nozzle causes boundary layer effects larger than usual for nozzles of this size. This paper discusses in detail the flow physics such as boundary layer growth and structure, and the effects of rarefaction. Furthermore a number of different domain sizes and exit boundary conditions are used to determine the optimum combination of computational time and accuracy.

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