磁控进气道二维性能计算
Numerical simulation of the two-dimensional magneto-hydro-dynamic controlled inlet
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摘要: 超燃冲压发动机进气道通常都是针对某一特定的马赫数进行设计的,当飞行马赫数不在设计马赫数时发动机性能急剧降低,磁控进气道的应用很有可能解决这一技术难题.对磁控进气道内的流动情况进行了二维数值模拟.飞行马赫数大于设计马赫数时采用磁控进气道可以调整激波位置使激波回到设计点,并减小燃烧室入口处的马赫数.分析了霍尔效应对磁控进气道性能的影响,结果表明分段电极可以有效减小霍尔效应的不利影响.
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关键词:
- 高超声速飞行器 /
- 超燃冲压发动机 /
- 磁流体动力学(MHD) /
- 磁控进气道 /
- 霍尔效应
Abstract: The numerical simulation of flows in magneto-hydro-dynamic(MHD) controlled inlet at flight Mach number larger than the design value was performed.The shocks could be moved back to the design point,and the outlet Mach number was decreased.Influence of load factor on the performance of MHD controlled inlet was analyzed.The role of the Hall Effect on MHD channel was investigated.The results show that continuous electrode Hall Effect causes serious performance deterioration,segmented electrode will efficiently reduce the adverse impact of Hall effect.-
Key words:
- hypersonic vehicle /
- scramjet /
- magneto-hydro-dynamic(MHD) /
- controlled inlet /
- Hall effect
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