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Evaluation of Specific Impulse for Liquid Rocket Engine Adopting Gas Generator Cycle  

Cho, Won-Kook (발사체엔진팀)
Seol, Woo-Seok (발사체엔진팀)
Publication Information
Aerospace Engineering and Technology / v.9, no.1, 2010 , pp. 93-97 More about this Journal
Abstract
The analysis of specific impulse of the liquid rocket engine employing gas generator cycle with LOx/kerosene as propellant has been performed. The relative error of performance of 300 ton level engine is 0.1%s for specific impulse and 12% for optimal combustion pressure comparing with the published data. The difference of the performance model and the material property models of gas generator product gas are the presumed major reason of discrepancy. The optimal condition of 30 ton level engine is combustion pressure of 68 bar and mixture ratio of 2.2 for maximum specific impulse. This optimal condition can be changed by performance models.
Keywords
gas generator cycle; systems analysis; specific impulse; liquid rocket engine; LOx/kerosene;
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