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展向截断曲面乘波压缩进气道气动布局

吴颖川 贺元元 余安远 乐嘉陵

吴颖川, 贺元元, 余安远, 乐嘉陵. 展向截断曲面乘波压缩进气道气动布局[J]. 航空动力学报, 2013, 28(7): 1570-1575.
引用本文: 吴颖川, 贺元元, 余安远, 乐嘉陵. 展向截断曲面乘波压缩进气道气动布局[J]. 航空动力学报, 2013, 28(7): 1570-1575.
WU Ying-chuan, HE Yuan-yuan, YU An-yuan, LE Jia-ling. Aerodynamic layout of spanwise truncated curved waverider compression inlet[J]. Journal of Aerospace Power, 2013, 28(7): 1570-1575.
Citation: WU Ying-chuan, HE Yuan-yuan, YU An-yuan, LE Jia-ling. Aerodynamic layout of spanwise truncated curved waverider compression inlet[J]. Journal of Aerospace Power, 2013, 28(7): 1570-1575.

展向截断曲面乘波压缩进气道气动布局

Aerodynamic layout of spanwise truncated curved waverider compression inlet

  • 摘要: 描述了所设计的展向截断曲面乘波压缩进气道.其特点是采用曲面乘波压缩前体,前体进气道压缩面基准流场由等熵压缩波轴对称流场组成,三维乘波面采用密切曲锥方法由前缘线各点流线跟踪拟合构成流面.乘波面根据飞行器和发动机的宽度要求进行了截断.数值计算和风洞试验结果表明:与相同几何收缩比的四波系压缩进气道相比,在马赫数为4.5时,曲面乘波压缩进气道流量系数提高12%,总压恢复系数提高39%;在马赫数为6时,曲面乘波压缩进气道流量系数提高4%,总压恢复系数提高50%.超然冲压发动机性能明显提高.

     

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出版历程
  • 收稿日期:  2012-07-07
  • 刊出日期:  2013-07-28

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