| 入口温度剖面对喷管流场结构的影响 |
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| 引用本文： | 王晓栋,乐嘉陵.入口温度剖面对喷管流场结构的影响[J].推进技术,2002,23(4):283-286. |
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| 作者姓名： | 王晓栋 乐嘉陵 |
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| 作者单位： | 中国空气动力研究与发展中心,四川,绵阳,621000 |
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| 摘 要： | 应用质量平均的Navier-Stokes方程和B－L代数湍流模型，对超燃冲压发动机尾喷管的流场进行了数值模拟研究，在计算过程中，对方程中的对流项采用了空间为二阶精度的TVD格式，扩散项则采用了二阶中心差分离散，通过数值模拟，对比研究了温度非均匀性，三维效应对尾喷管的流场结构的影响。
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| 关 键 词： | 温度 喷管 流场结构 影响 高超音速冲压发动机 流动分布 |
| 文章编号： | 1001-4055(2002)04-0283-04 |
| 修稿时间： | 2001年8月23日 |
Effect of temperature profile at entrance on flow-fields of nozzle |
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| WANG Xiao,dong and LE Jia,ling.Effect of temperature profile at entrance on flow-fields of nozzle[J].Journal of Propulsion Technology,2002,23(4):283-286. |
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| Authors: | WANG Xiao dong and LE Jia ling |
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| Institution: | China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China |
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| Abstract: | The flow fields within a nozzle of scramjet engine were simulated numerically by the Faver Averaged Navier Stokes equation with the Baldwin Lomax algebraic turbulence model The second order Yee H C TVD scheme was used for the inviscid flux terms and a central difference considering the character of flow was used for the diffusion terms During the simulation,the effect of temperature no uniformity and of 3 D effectiveness on the flow fields was investigated contrastively |
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| Keywords: | Hypersonic ramjet engine Nozzle flow Flow distribution Numerical simulation Navier Stokes equation |
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