| 引用本文: | 潘余,王振国.激波对超声速流中横向射流的影响.[J].国防科技大学学报,2007,29(6):6-9.[点击复制] |
| PAN Yu,WANG Zhenguo.Shock Impinge on Supersonic Cross Flow Injection[J].Journal of National University of Defense Technology,2007,29(6):6-9[点击复制] |
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| 激波对超声速流中横向射流的影响 |
| 潘余, 王振国 |
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(国防科技大学 航天与材料工程学院，湖南 长沙 410073)
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| 摘要: |
| 为了揭示激波对超声速流中横向射流的影响，在超声速流中利用长9mm、坡度为23°的斜坡产生激波。组合利用高速摄影仪和纹影仪拍摄激波入射在气体和液体射流的不同位置，以及相同位置不同喷注压降时的流场纹影和阴影图像。结果表明，激波对气体和液体横向射流的影响基本相同，都表现为入射激波增强了湍流度，扩大了燃料空间发展区域，增强了与主流的混合，激波入射在射流的前部比射流的后部影响大。 |
| 关键词: 超声速燃烧冲压发动机 横向射流 激波 |
| DOI： |
| 投稿日期：2007-05-21 |
| 基金项目:国家863高技术资助项目(2005AA721051) |
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| Shock Impinge on Supersonic Cross Flow Injection |
| PAN Yu, WANG Zhenguo |
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(College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China)
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| Abstract: |
| To investigate the shock impingement on vertical injection in supersonic flow, shock was produced by a 9mm long, 23° angle wedge. The images of shocks impinged at different position and pressure of gas and liquid injection were achieved by using both a high speed camera and a schlieren system. Results revealed that gas and liquid injection almost have similar phenomena, that is, impinged by the shock, fuel turbulent intensity will increase, fuel distribution area will be larger in supersonic flow, spreading more quickly into the main supersonic flow, and the shock impinged at the foreside affect more than rearward of injection. |
| Keywords: scramjet vertical injection shock |
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