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多级压缩锥导/吻切锥乘波体设计与对比分析

吕侦军 王江峰

吕侦军, 王江峰. 多级压缩锥导/吻切锥乘波体设计与对比分析[J]. 北京航空航天大学学报, 2015, 41(11): 2103-2109. doi: 10.13700/j.bh.1001-5965.2014.0740
引用本文: 吕侦军, 王江峰. 多级压缩锥导/吻切锥乘波体设计与对比分析[J]. 北京航空航天大学学报, 2015, 41(11): 2103-2109. doi: 10.13700/j.bh.1001-5965.2014.0740
LYU Zhenjun, WANG Jiangfeng. Design and comparative analysis of multistage compression cone-derived waverider and osculating cone waverider[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2103-2109. doi: 10.13700/j.bh.1001-5965.2014.0740(in Chinese)
Citation: LYU Zhenjun, WANG Jiangfeng. Design and comparative analysis of multistage compression cone-derived waverider and osculating cone waverider[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2103-2109. doi: 10.13700/j.bh.1001-5965.2014.0740(in Chinese)

多级压缩锥导/吻切锥乘波体设计与对比分析

doi: 10.13700/j.bh.1001-5965.2014.0740
基金项目: 江苏高校优势学科建设工程项目
详细信息
    作者简介:

    吕侦军(1987-),男,江苏泰州人,博士研究生,lzhj1987124@126.com

    通讯作者:

    王江峰(1970-),男,江苏南京人,教授,wangjf@nuaa.edu.cn,主要研究方向为高超声速飞行器布局设计、燃烧流场数值模拟技术、气动加热计算技术等.

  • 中图分类号: V221+.3

Design and comparative analysis of multistage compression cone-derived waverider and osculating cone waverider

  • 摘要: 将乘波体作为以吸气式超燃冲压发动机为动力的高超声速飞行器的前体,不仅可以发挥乘波体优异的气动力性能,而且起到了高超声速飞行器前体对来流的预压缩作用.为了进一步提升乘波前体的预压缩作用,基于Sobieczky提出的吻切锥原理,发展了一种新的多级压缩乘波体外形的设计方法.将该设计方法应用到锥导和吻切锥乘波体的设计中,生成了具有多个压缩面的多级压缩锥导和吻切锥乘波体,同时对相同设计条件和具有相同投影曲线的前缘条件下获得的三级压缩锥导和吻切锥乘波体的性能进行了对比分析.研究结果表明数值模拟计算结果与设计预期完全吻合,该多级压缩乘波体设计方法可以应用于锥导和吻切锥乘波体.

     

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出版历程
  • 收稿日期:  2014-11-27
  • 修回日期:  2015-01-04
  • 网络出版日期:  2015-11-20

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