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http://dx.doi.org/10.5139/JKSAS.2005.33.5.072

Performance test of micronozzle  

Moon, Seong-Hwan (충남대학교 항공우주공학과 대학원)
Oh, Hwa-Young (충남대학교 항공우주공학과 대학원)
Huh, Hwan-Il (충남대학교 항공우주공학과)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.33, no.5, 2005 , pp. 72-78 More about this Journal
Abstract
We conducted the performance test of micronozzle having nozzle throat diameter of 1.0, 0.5, 0.25 mm in an ambient pressure. We used N2 gas as a cold gas propellant. We varied chamber pressure from 2 to 20 bar and measured the thrust and mass flow rate. Through the test, we concluded that viscous losses were increased with decreasing chamber pressure. We found that micronozzle performance was higher than orifice performance through thrust comparison.
Keywords
Micronozzle; Cold gas thruster; Thrust measurement; Viscous loss;
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