摘要
数值模拟采用基于 Van Leer的矢通量分裂格式 ;应用线 Gauss- Seidel迭代法求解 ;并结合局部时间步长技术对收敛过程加速。对 Re=1 .66× 1 0 6
The thin layer N S equations and Baldwin Lomax algebraic turbulence model are used to calculate the transonic turbulent flow in a forward nozzle. The numerical algorithm is based on the implicit finite volume form of Van Leer flux vector splitting schemes in generalized coordinates. A line Gauss Seidel relaxation is used to invert the coefficient matrix by alternating sweep, and the local time stepping is implemented to accelerate the convergence rate of steady problems. A flow field with the Reynolds number of 1 66×10 6 is simulated, and the results are consistent with the experimental data.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1996年第4期431-434,共4页
Acta Aeronautica et Astronautica Sinica
关键词
迎风格式
喷管效率
湍流
流场
upwind schemes flux vector splitting finite element method nozzle efficiency
