| 超声速进气道流场三维数值模拟 |
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| 引用本文： | 张永芝,李卓,李海龙.超声速进气道流场三维数值模拟[J].火箭推进,2008,34(3):27-30. |
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| 作者姓名： | 张永芝 李卓 李海龙 |
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| 作者单位： | 1. 内蒙古工业大学理学院,内蒙古,呼和浩特,010051
2. 内蒙古动力机械研究所,内蒙古,呼和浩特,010010 |
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| 摘 要： | 超声速进气道是固体火箭冲压发动机至关重要的部件之一,直接影响燃烧室的燃烧及发动机性能。基于N-S方程、标准k-ε双方程湍流模型,利用FLUENT软件对某型固体火箭冲压发动机楔形超声速进气道内外流场进行了三维数值模拟。计算得到了超声速进气道在飞行马赫数为Ma=3.5的情况下的流场性能。并在相同马赫数下,研究了等比压缩和攻角条件下的进气道流场的分布情况。模拟结果表明：进气道的总压恢复系数和流量系数等性能指标受到攻角的影响而发生变化。
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| 关 键 词： | 固体火箭冲压发动机 进气道 模拟仿真 攻角 缩比 |
Three dimension numerical simulation of the supersonic inlet flowfield |
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| Zhang Yongzhi,Li Zhuo,Li Hailong.Three dimension numerical simulation of the supersonic inlet flowfield[J].Journal of Rocket Propulsion,2008,34(3):27-30. |
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| Authors: | Zhang Yongzhi Li Zhuo Li Hailong |
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| Institution: | Zhang Yongzhi1,Li Zhuo2,Li Hailong2 (1 Inner Mongolia University of Technology,Inner Mongolia 010051,China,2 Inner Mongolia Dynamical Machine Acedemy,Inner Mongolia 010010,China) |
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| Abstract: | Supersonic inlet is one of the important part of solid rocket ramjet. The performance research of this inlet is one of the key techniques for solid rocket ramjet. The performance of supersonic inlet determines the pressure and the air flux in combustor, then affects the work of ramjet. In this paper, based on the N-S equation, standard k-ε turbulence model, FLUENT is used to simulate the cuniform air inlet of solid rocket ramjet. The flow field of air inlet at Mach number 3.5 is gained. Under the same Mach number, some researches on the performance of flow field of air inlet with attack angle and compression ratio with body are also performed. The simulation results indicated that total pressure recovery coefficient and mass flow coefficient of air inlet are effected by changing attack angle. |
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| Keywords: | solidrocketramjet supersonicinlet numericalsimulation attackangle compres-sionratio |
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