超声速内流道摩擦阻力分析及减阻技术研究

Shuai Wang, Guoqiang He, Fei Qin, Xianggeng Wei

科研成果: 期刊稿件文章同行评审

13 引用 (Scopus)

摘要

In a constant-cross-confined-space with rearward facing steps, the skin-friction drag and drag reduction technics in a supersonic inner flow path was developed by three-dimensional numerical simulation. The influential mechanism of skin-friction drag in the same mass hydrogen injection and combustion but under different air inlet conditions and combustor entry conditions when the scramjet engine operated from flight Mach number 5, 6, 6.5 and 7, and different injecting pressure effects on the wall shear stress beheading the injectors were analyzed and compared. The results show that the drag reduction effect under low injection speed is more obvious than that under high injection speed. 507kPa obtains 10% drag reduction and 50.7kPa obtains 5%. Boundary layer combustion achieves almost 70% drag reduction. When the fluid passes backward facing step, regularly uneven changes of wall shear stress will appear and the biggest difference is 100%. The trends of wall shear stress and density are basically the same. Therefore, the key point of skin-friction drag reduction in inner flow path is building low density field near the wall surface. The area with stable and effective drag reduction effect is located more backwards of the injectors. However, due to the mixing and consumption of fuel, the drag reduction effect gradually decreases along the flow direction.

投稿的翻译标题Research on skin-friction drag and drag reduction technics in a supersonic inner flow path
源语言繁体中文
页(从-至)908-919
页数12
期刊Hangkong Dongli Xuebao/Journal of Aerospace Power
34
4
DOI
出版状态已出版 - 1 4月 2019

关键词

  • Boundary layer combustion
  • Drag reduction
  • Skin-friction drag
  • Supersonic inner flow path
  • Wide-speed-range

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