| 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。 |
| 关键词: 高超音速冲压发动机 喷管气流 流动分布 数值仿真 纳维尔-斯托克斯方程 |
| DOI： |
| 分类号:V233.7 |
| 基金项目: |
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| Effect of temperature profile at entrance on flow-fields of nozzle |
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WANG Xiao dong, LE Jia ling
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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 |
| Key words: Hypersonic ramjet engine Nozzle flow Flow distribution Numerical simulation Navier Stokes equation |
