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。
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
出处
《推进技术》
EI
CAS
CSCD
北大核心
2002年第4期283-286,共4页
Journal of Propulsion Technology
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
Hypersonic ramjet engine
Nozzle flow
Flow distribution
Numerical simulation
Navier Stokes equation
