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Chuang Zhou, Nanjia Yu, Shuwen Wang, Shutao Han, Haojie Gong, Guobiao Cai and Jue Wang
Liquid rocket engines with hydrogen peroxide and kerosene have the advantages of high density specific impulse, high reliability, and no ignition system. At present, the cooling problem of hydrogen peroxide engines, especially with regenerative cooling, ...
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Xiaobing Wang, Junqiang Wu, Jianzhong Chen, Yuping Li, Zhongliang Zhao, Guangyuan Liu, Yang Tao and Neng Xiong
Cryogenic wind tunnels provide the for possibility aerodynamic tests to take place over high Reynolds numbers by operating at a low gas temperature to meet the real flight simulation requirements, especially for state-of-the-art large transport aircrafts...
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Kai Dresia, Eldin Kurudzija, Jan Deeken and Günther Waxenegger-Wilfing
Accurate calculations of the heat transfer and the resulting maximum wall temperature are essential for the optimal design of reliable and efficient regenerative cooling systems. However, predicting the heat transfer of supercritical methane flowing in c...
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Jian Liu, Mengyao Xu, Pengchao Liu and Wenxiong Xi
At an extremely high Mach number, the regenerative cooling of traditional kerosene cannot meet the requirement of the heat sink caused by aerodynamic heating and internal combustion in a scramjet propulsion system. As a supplement of traditional regenera...
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Wei Zhao, Xinglian Yang, Jingying Wang, Yongkang Zheng and Yue Zhou
Significant thermochemical nonequilibrium effects always exist in the flow field around hypersonic vehicle at extreme flight condition. Previous studies have proposed various thermodynamic and chemical kinetic models to describe the thermochemical nonequ...
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