摘要
应用隐式矢通量分裂差分格式结合改进的Baldwin－Lomax湍流模型直接求解时间平均Navier－Stokes方程组，对扩压器跨声流动进行了数值计算，准确地捕获了激波，预测了由于强激波作用引起的湍流边界层分离现象，与实验数据比较，结果令人满意。数值实验表明：该方法具有精度高、稳定性好、计算量少、收敛快等优点，计算结果可用于高速飞行器气动特性的研究。
An implicit flux vector splitting scheme, companying with the modified Baldwin-Lomax turbulence model,has been provided to solve the time-average Navier-Stokes equations directly. In the calculation of two-dimensional transonic diffuser, shock wav e is exactly captured, boundary-layer separation induced by shock is also predicted.The results are satis-fied.Numerical calculations detnonstrate clearly that it has obvious super-iorities in aspects of accuracy, robutness, calculation time and convergence.The resulting data can be employed to analyzing of high-speed vehicles aerodynamic characteristics.
出处
《空气动力学学报》
CSCD
北大核心
1997年第2期256-260,共5页
Acta Aerodynamica Sinica
基金
国家自然科学基金
关键词
扩压器
激波
边界层
分离
数值方法
航空发动机
diffuser
numerical simulation
shock waye
boundary-layer separation
