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《Missiles and Space Vehicles》 2008-03
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Aero-Heating Analysis for Hypersonic Blunt-Headed Body

Lü Hongqing,Wang Zhenqing,Wang Yongjun,Zhang Cuie,Jin Chengbin(Department of Space Engineering,Harbin Engineering University,Harbin,150001)  
Taking hypersonic reentry body as an example,the boundary-layer edge parameters are determined by solving Euler equations.The heating flux density of warhead at zero attack angle is calculated by using reference enthalpy method basing on theory and semi-empirical,and the heat proof effect of blunt leading edge is proved by the temperature curve.Based on this,the temperature field along thickness for stagnation region is analyzed by using finite-element method,which provides a reference for heat proof design of the heat protectetion design of reentry body.
【Fund】: 高等学校博士学科点专项科研基金(20060217010)资助
【CateGory Index】: TJ760.12
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【Citations】
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【Co-citations】
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1 ZHU Dongmei,LIU Guoyong,LI Mouwei,ZHANG Shaojun School of Mechanical Engineering,University of Science and Technology Beijing,Beijing 100083;Heat residual stress control during steel plate controlled-cooling process[J];Journal of University of Science and Technology Beijing;2008-08
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