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高超进气道的反设计和阻力特性分析

张堃元   

  1. 南京航空航天大学
  • 收稿日期:2014-09-11 修回日期:2014-09-17 发布日期:2014-09-17
  • 通讯作者: 张堃元
  • 基金资助:
    基于联合决策与估计的高频超视距雷达信息处理与融合(国家自然基金重点项目)

Reverse Design and Drag Characteristic of Hypersonic Inlet

kun-yuan zhang   

  • Received:2014-09-11 Revised:2014-09-17 Published:2014-09-17
  • Contact: kun-yuan zhang
  • Supported by:
    National Natural Science Foundation of China

摘要: 提出了曲面激波压缩系统的新概念,即利用特殊设计的楔形曲面压缩面或空间曲面压缩面,产生一系列与前缘弱激波相互交汇或叠加的压缩波系,从而使前缘激波弯曲,形成特殊的弯曲激波,它与波后的等熵压缩波来共同完成对气流的压缩。在此基础上实现了由给定出口气动参数的超声速内流道反设计,实现了由指定压缩面压力分布p(s)、指定压缩面马赫数分布Ma(s)要求的型面反设计,实现了由指定激波波面W(s)的压缩型面反设计。研究证明,曲面压缩-曲面激波压缩系统具有良好的综合气动性能,为高性能高超声速进气系统的气动设计提供了一种全新的设计方法。 减阻是高超声速进气道面临的另一难题,本文运用基本气动理论分析了高超声速进气道可能的最小阻力和减阻设计方向,为飞行器总体设计、动力系统总体设计和进气道减阻研究提供了科学依据。

关键词: 高超声速进气道, 反设计, 弯曲激波压缩系统, 进气道阻力, 变几何进气道

Abstract: This paper proposed the new concept of curved shock compression system, in which specially designed 2D or 3D curved compression surface is used. The leading shock wave would be curved due to its interaction with isentropic compression waves near the compression surface, and free stream is compressed by the curved shock wave together with the isentropic waves. Based on this concept, methods of: reverse designing supersonic internal flow path according to assigned outflow parameters, reverse designing compression surface according to pressure distribution p(s) or Mach number distribution Ma(s) along the surface, and reverse designing surface according to shock wave shape W(s) are established. The curved shock compression has a good comprehensive performance as shown in the investigation, and represents a brand-new approach for the design of hypersonic propulsion compression system. Drag reduction is another challenge for hypersonic inlet design. Based on gas dynamics fundamentals, the minimum possible value of inlet drag is derived determined and drag reduction principles are proposed, which could be scientific basis for future flight vehicle designing, propulsion system designing and inlet drag reduction investigation.

Key words: hypersonic inlet, reverse design, curved shock compression system, inlet drag, geometry variable inlet

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