Kakuda Research Center, National Aerospace Laboratory(NAL)
Kakuda Research Center, National Aerospace Laboratory(NAL)
Kakuda Research Center, National Aerospace Laboratory(NAL)
Kakuda Research Center, National Aerospace Laboratory(NAL)
Kakuda Research Center, National Aerospace Laboratory(NAL)
Kakuda Research Center, National Aerospace Laboratory(NAL)
Kakuda Research Center, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
Technical Report of National Aerospace Laboratory TR-1062T
Combustion tests were conducted using liquid oxygen(LOX)/gaseous hydrogen, LOX/gaseous methane and LOX/RJ-1J as propellants. Two water-cooled calorimetric combustors and two types of injectors, i.e., a coaxial and an impinging injector, were used. The maximum chamber pressure was 10MPa and the heat flux reached 100MW/m2 in the maximum. Heat flux values measured at the throat section were lower than those predicted by the simplified Bartz's equation. A modified Bartz's equation, which uses 0.023 as a coefficient (instead of 0.026 as in the original) and which takes into account the injector and effect as well as the film cooling effect, more accurately predicted the measured heat flux distribution of the coaxial type injector. With regard to LOX/RJ-1J propellants, an empirical correlation for the thermal resistance of the carbon layer deposited on the chamber wall was obtained. It was observed that the values of thermal resistance measured were a small percentage of the values found in previously published data.
Hot Gas Side Heat Transfer Characteristics of LOX/H2 and LOX/HC Type Propellats
naltr1062t.pdf
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