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

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