北京航空航天大学学报 ›› 2015, Vol. 41 ›› Issue (11): 2103-2109.doi: 10.13700/j.bh.1001-5965.2014.0740

• 论文 • 上一篇    下一篇

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   

  1. 南京航空航天大学航空宇航学院, 南京 210016
  • 收稿日期:2014-11-27 修回日期:2015-01-04 出版日期:2015-11-20 发布日期:2015-12-01
  • 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. E-mail:angjf@nuaa.edu.cn
  • 作者简介:吕侦军(1987-),男,江苏泰州人,博士研究生,lzhj1987124@126.com
  • 基金资助:
    江苏高校优势学科建设工程项目

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

LYU Zhenjun, WANG Jiangfeng   

  1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
  • Received:2014-11-27 Revised:2015-01-04 Online:2015-11-20 Published:2015-12-01

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.

关键词: 气动布局, 高超声速, 多级压缩, 锥导乘波体, 吻切锥乘波体

Abstract: As a forebody of hypersonic vehicle which was powered by air-breathing scramjet, waverider not only showed its excellent aerodynamic performance, but also played the role of pre-compression to incoming flow for hypersonic vehicle. In order to further enhance the waverider forebody's pre-compression effect, a new design method for multistage compression waverider configuration was presented, based on theory of osculating cone proposed by Sobieczky. Multistage compression cone-derived waverider and osculating cone waverider which had multiple compressive surfaces were obtained by using the design method. Aerodynamics performance of three-stage compression cone-derived waverider and osculating cone waverider were compared and analyzed in the same design condition and with the same projection curve of forbody. The research results show that the design expectation is in well agreement with the result of numerical simulation. The design method of multistage compression waverider can be used to cone-derived waverider and osculating cone waverider.

Key words: aerodynamic configuration, hypersonic, multistage compression, cone-derived waverider, osculating cone waverider

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