摘要
本文工作是在 Mac Cormack通量分裂格式 [2 ] 基础上发展的一种有限面积通量分裂隐式格式 ,其特点是在求解隐式离散化方程时 ,采用往返扫描一次的 Gauss- Seidel线松驰迭代方法 ,避免了对时间步长的任何限制。为提高定常解精度 ,格式的显式右端项采用二阶精度的离散。在数值求解跨音速涡轮平面叶栅问题中 ,对壁面边界作了较仔细的隐式处理。数值计算表明本方法保持了 Mac Cormack格式具有的高收敛速率 ,(约 30个时间步即可达到定常解 )而每一时间步计算量约减少一半。数值结果与实验结果符合得很好。
MacCormack′s flux splitting method has proven itself guite fast converging in numerical simulation of flows in converging-diverging nozzle.In this paper a development on the basis of this method is presented for Euler equations in order to obtain numerical solutions of inviscid transonic flow through a two-dimensional turbine cascade.In the present finite-area flux splitting implicit method the Gauss-Seidel line relaxation recommended by R.W.MacCormack is applied to solving the implicit descretization equations.But we abandon the predictor-corrector two-step method to cut down the computational time in every time-step,because it cannot enhance the accuracy of the steady soluton in flux-splitting methods.In our practical computation,in order to improve the accuracy of the solution,the right side of the difference equation is discretized to be of second order accuracy,the blade wall boundary conditions and the numerical results show that the present method retains the effective convergence rate (only about 30 timesteps to attain a steady solution)and yield numerical solutions conformable with the experimental results.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1989年第4期319-324,共6页
Journal of Aerospace Power
