航空学报 > 2016, Vol. 37 Issue (9): 2711-2720   doi: 10.7527/S1000-6893.2016.0017

压力分布可控的高超声速进气道/前体一体化乘波设计

李怡庆1, 韩伟强1, 尤延铖1, 潘成剑2   

  1. 1. 厦门大学 航空航天学院, 厦门 361005;
    2. 北京空天技术研究所, 北京 100074
  • 收稿日期:2015-09-09 修回日期:2015-10-25 出版日期:2016-09-15 发布日期:2016-02-23
  • 通讯作者: 尤延铖 男, 博士。主要研究方向:航空宇航推进理论与工程。 Tel.: 0592-2186849 E-mail: yancheng.you@xmu.edu.cn E-mail:yancheng.you@xmu.edu.cn
  • 作者简介:李怡庆 男, 博士研究生。主要研究方向:高超声速进气系统设计。 Tel.: 0592-2186849 E-mail: yiqingxmu@163.com
  • 基金资助:

    国家自然科学基金(91441128,51276151);国防基础科研项目(B1420133058)

Integration waverider design of hypersonic inlet and forebody with preassigned pressure distribution

LI Yiqing1, HAN Weiqiang1, YOU Yancheng1, PAN Chengjian2   

  1. 1. School of Aeronautics and Astronautics, Xiamen University, Xiamen 361005, China;
    2. Beijing Aerospace Technology Institute, Beijing 100074, China
  • Received:2015-09-09 Revised:2015-10-25 Online:2016-09-15 Published:2016-02-23
  • Supported by:

    National Natural Science Foundation of China(91441128, 51276151); National Defense Basic Scientific Research(B1420133058)

摘要:

在二维弯曲激波高超声速进气道基础上,发展了一种压力可控的进气道/前体一体化乘波设计方法。通过事先指定前体/进气道壁面压力分布,结合二维特征线反设计方法,可以逆向设计出流向、横向压力分布规律都可控的进气道/前体外压缩段型面。采用该方法,设计了一种二维进气道/前体一体化方案,并对其进行数值模拟。结果表明:设计状态下,与不带侧板二维进气道相比,此类一体化方案中的进气道设计状态流量系数提高27%,出口压比提高48.5%,总压恢复系数提高10%;与楔导乘波理论设计的一体化方案相比,压力可控的一体化方案具有相似的外形尺寸和乘波特性,但进气道流量系数则较楔导乘波方案提高了5%,进气道出口压比提高6.4%,总压恢复系数提高2.3%。

关键词: 高超声速, 进气道/前体一体化, 压力分布, 乘波理论, 二维高超声速进气道

Abstract:

On the basis of two-dimensional curved shock hypersonic inlets, a new integration,waverider design, of hypersonic inlet and forebody with preassigned pressure distribution is presented. A proper streamwise pressure distribution is assigned as the first step according to the shape of a curved shock wave. Afterwards, the external compression part of the inlet and forebody with controllable wall pressure distribution could be designed using the inverse two-dimensional method of characteristics. An integrated configuration is then derived from this concept and numerically studied. The results show that, on the design point, the flow capture ratio of the integrated configuration is enhanced by 27% compared with the pure two-dimensional inlet without sidewalls. The pressure ratio coefficient of inlet outflow rises by 48.5%, and the total pressure recovery coefficient is 10% higher than the no-sidewall inlet. In addition, compared with the Caret integration case, although with the same geometry shape and waverider character,the performance of mass flow rate, pressure ratio and total pressure recovery coefficient are 5%, 6.4%, and 2.3% improved, respectively.

Key words: hypersonic, inlet and forebody integration, pressure distribution, waverider concept, two-dimensional hypersonic inlet

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