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)
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)
Kakuda Research Center, National Aerospace Laboratory(NAL)
Ishikawajima-Harima Heavy Industries Co., Ltd.
Ishikawajima-Harima Heavy Industries Co., Ltd.
Ishikawajima-Harima Heavy Industries Co., Ltd.
Ishikawajima-Harima Heavy Industries Co., Ltd.
Ishikawajima-Harima Heavy Industries Co., Ltd.
Ishikawajima-Harima Heavy Industries Co., Ltd.
Ishikawajima-Harima Heavy Industries Co., Ltd.
Ishikawajima-Harima Heavy Industries Co., Ltd.
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-1149
A series of experiments was conducted for studying scramjet nozzle performance under Mach 8 flight conditions using high temperature gas flow with Mach 2.5. Monomethyl-hydrazine(MMH) and nitrogen tetraoxide(NTO) were adopted to produce high temperature gas flow. The stagnation temperature was designed to be 3170K, and the stagnation pressure to be 1 Mpa. A simple configuration by plane walls was selected for the scramjet nozzle. Thrust by the srramjet nozzle with expansion ratios of 3(EN3) and 5(EN5) was examined. The experiments were performed using a thrust measuring system installed in a high altitude test facility. Delivered specific impulse (ISP) by MMH/NTO combustion was found to be 17.3 sec (EN3) to 26.1 sec (EN5). These small increments of Isp in the scramjet nozzles, however, correspond to Isp gains of about 1100 sec for H2 fueled scramjets. Performances of nozzles were predicted using computer codes, and energy release loss, kinetic loss and two-dimensional loss were identified. The two-dimensional loss was predicted to be 16.5％ in the EN3 nozzle and to decrease to 7.0％ in the EN5 nozzle. The kinetic loss due to chemical freezing was found to be 4.4％ (EN3) and 3.0％ (EN5). The nozzle performance could be compared with the experimental results. A friction loss (12.4％) measured by thrusts suggested laminar flow in the scramjet nozzle used in the MMH/NTO experiments. Measured heat flux on nozzles also supported the laminar boundary layer. Experiments using a cold gas flow with the scramjet nozzles were also conducted to compare with the hot flow.
スクラムジェットノズルの研究その1 2次元ノズルの性能
naltr01149.pdf
(4.58MB)
