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弹箭与制导学报 >

2015 , Vol. 35 >Issue 4: 137 - 140,144

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2015.04.034

弹道与气动力技术

头部两侧进气道特性分析

  • 邵跃跃 ,
  • 孙振华 ,
  • 马高建
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  • 中国空空导弹研究院,河南洛阳 471009

邵跃跃(1990-),男,安徽亳州人,硕士研究生,研究方向: 航空宇航推进理论与工程。

收稿日期: 2014-08-12

  网络出版日期: 2025-05-26

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Performance Analysison Bilateral Inlet of Head

  • SHAO Yueyue ,
  • SUN Zhenhua ,
  • MA Gaojian
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  • China Airborne Missile Academy, Henan Luoyang 471009, China

Received date: 2014-08-12

  Online published: 2025-05-26

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摘要

对一种定几何混压式头部两侧布局进气道进行了三维数值模拟。研究了进气道不同来流条件下的流场结构分布以及这些条件对进气道性能的影响,并与风洞试验结果进行了对比。结果表明,进气道内靠近内侧角部区域激波与附面层干涉比较明显;随着来流马赫数变化,进气道总压恢复系数降低,流量系数上升;攻角状态下进气道内附面层发展较快,对性能影响较大。

关键词： 固冲发动机; 进气道; 风洞试验; 数值模拟; 附面层

本文引用格式

邵跃跃 , 孙振华 , 马高建 . 头部两侧进气道特性分析[J]. 弹箭与制导学报, 2015 , 35(4) : 137 -140,144 . DOI: 10.15892/j.cnki.djzdxb.2015.04.034

Abstract

Three-dimensional flow of fixed-geometry inlet of ducted rocket with a head-bilateral inlet configuration was simulated numerically. The influence of coming flow condition on performance and flow field of the inlet was investigated as well as the results were compared with wind tunnel experiment data. The results show that interference of shock wave and boundary layer is obvious in the corner near underside; With increase of free stream Mach number, the total pressure recovery coefficient decreases, while the coefficient of mass flow ascends; The boundary layer has a great influence on flow field of the inlet with an angle-of-attack.

Key words： solid rocket ramjet; inlet; wind tunnel experiment; numerical simulation; boundary layer

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参考文献

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