推进技术 ›› 2014, Vol. 35 ›› Issue (9): 1162-1167.

• 气动热力学 总体 • 上一篇    下一篇

超声速铲形进气道数值计算及试验研究

李宏东1,朱 璞1,王永卫1,朱守梅1,2,王 健1,2,刘汉斌3   

  1. 北京动力机械研究所,北京 100074;北京动力机械研究所,北京 100074;北京动力机械研究所,北京 100074;北京动力机械研究所,北京 100074;北京动力机械研究所 高超声速冲压发动机技术重点实验室,北京 100074;北京动力机械研究所,北京 100074;北京动力机械研究所 高超声速冲压发动机技术重点实验室,北京 100074;二炮驻31所军代表室,北京 100074
  • 发布日期:2021-08-15
  • 作者简介:李宏东(1977—),高级工程师,研究领域为进气道设计。

Numerical Computation and Test for Supersonic Shovel Inlet

  1. Beijing Power Machinery Institute,Beijing 100074,China;Beijing Power Machinery Institute,Beijing 100074,China;Beijing Power Machinery Institute,Beijing 100074,China;Beijing Power Machinery Institute,Beijing 100074,China;Science and Technology on Scramjet Laboratory,Beijing Power Machinery Institute,Beijing 100074,China;Beijing Power Machinery Institute,Beijing 100074,China;Science and Technology on Scramjet Laboratory,Beijing Power Machinery Institute,Beijing 100074,China;The second Artillery Representative Office in the 31st Research Institute,Beijing 100074,China
  • Published:2021-08-15

摘要: 为了研究超声速铲形进气道的气动特性,针对固定几何超声速铲形进气道,利用数值仿真计算及风洞试验,获得了来流马赫数Ma∞=2.5,3.0,3.5,4.0,攻角α=-6°,-3°,0°,3°,6°,8°以及侧滑角β=3°,6°的临界性能。研究结果表明该超声速进气道具有良好的攻角特性,随着攻角的增加,总压恢复系数和流量系数增加;6°侧滑角以内进气道总压恢复系数和流量系数变化量很小。该进气道与飞行器前体一体化设计,能够很好地适应大空域、宽马赫数范围工作需求。

关键词: 飞行器/进气道一体化;冲压发动机;进气道;数值计算;风洞试验

Abstract: Numerical computation and wind tunnel test for supersonic shovel inlet with fixed geometry is carried out with different incoming Mach numbers(2.5,3.0,3.5,4.0),different angles of attack(-6°,-3°,0°,3°,6°,8°)and different angles of the sideslip(3°,6°). The results indicate that this supersonic inlet has good attack angle characteristic. Inlet mass-flow coefficient and inlet total pressure recovery coefficient increase with increasing angle of attack. Inlet mass-flow coefficient and inlet total pressure recovery coefficient vary very small within 6°angle of the sideslip. This inlet is integrated with the vehicle,and it can be well suited with large airspace and wide Mach number.

Key words: Vehicle-inlet integration;Ramjet engine;Inlet;Numerical computation;Wind tunnel test