| 摘要: |
| 为明确高超声速进气道内部阻力的特点,并为进气道减阻设计提供参考依据,以侧压式进气道为例,分别以内壁面和捕获流管为分析体,讨论进气道不同几何设计参数下的阻力特性;以数值模拟为手段,给出了总阻力的大小及各项阻力的分配比例,并分析了进气道几何参数变化对阻力的影响关系。给出了侧压式进气道附加阻力作用表面的形状,讨论了附加阻力的特点。研究发现,内壁面总阻力中,压力阻力随收缩比增加而增加,约占总阻力的60%到70%;唇口前的溢流会产生“附加推力”而不是通常情况的附加阻力。 |
| 关键词: 高超声速进气道 阻力 阻力分配+ |
| DOI： |
| 分类号:V231.3 |
| 基金项目:国家“八六三”基金(2005AA723020) |
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| Parametric analysis of internal drag in sidewall-compression inlet |
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Coll.of Energy and Power Engineering,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China
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| Abstract: |
| The influence of different geometry parameters to the internal drag of sidewall-compression inlets was presented to specify the drag characteristics of scramjet.The wall inside of the inlet and capture flow tubes were used respectively to analyze drag.The total drag and component of different internal drag were given through numerical investigation.The relationship between geometry parameters of inlets to the characteristics of internal drag was discussed.The feature of the stream-surface on which additive drag acts was investigated.It is found that pressure drag increases with contraction ratio. The proportion of pressure drag to the total internal drag ranges from 60% to 70%.It is surprised that the additive drag becomes "additive thrust" in sidewall-compression inlet. |
| Key words: Hypersonic inlet Drag Drag distribution+ |
