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A Study on Combustion Characteristic with the Variation of Oxidizer phase in Hybrid Rocket Motor using PE/$N_2O$  

Lee, Jung-Pyo (한국항공대학교 항공우주 및 기계공학과)
Kim, Gi-Hun (한국항공대학교 항공우주 및 기계공학부)
Kim, Soo-Jong (한국항공대학교 항공우주 및 기계공학과)
Kim, Hak-Chul (한국항공대학교 항공우주 및 기계공학부)
Moon, Hee-Jang (한국항공대학교 항공우주 및 기계공학과)
Sung, Hong-Gye (한국항공대학교 항공우주 및 기계공학부)
Kim, Jin-Kon (한국항공대학교 항공우주 및 기계공학과)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.14, no.2, 2010 , pp. 46-53 More about this Journal
Abstract
The purpose of this paper is to study combustion characteristics with the different phase of oxidizer in hybrid rocket combustion. HDPE(High Density Polyethylene) as fuel and $GN_2O$(Gas $N_2O$), $LN_2O$(Liquid $N_2O$) as oxidizer were used to perform the experiments. An investigation was performed for a change of the regression rate, pressure of combustion chamber and combustion efficiency according to the variation of oxidizer phase. In case of using $LN_2O$ as oxidizer, the regression rate is not significantly different from using $GN_2O$ as oxidizer. It is considered that combustion energy is much larger than latent heat energy which was used in the evaporation of liquid oxidizer. However propulsion performance efficiency for $LN_2O$ showed lower value than for $GN_2O$. By increasing the flow rate of liquid oxidizer, heat transfer needed for vaporization of liquid oxidizer was increased, which resulted in the growth of combustion instability.
Keywords
Hybrid Rocket; $LN_2O$; $GN_2O$; Regression Rate; Latent Heat; $c^*$;
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