二元喷管跨音速流场的数值计算  

DIGITAL SIMULATION OF TRANSONIC FLOW FIELDS IN A PLANAR NOZZLE

作　　者：郑小清[1] 曾军 

机构地区：[1]西北工业大学

出　　处：《航空动力学报》1992年第4期312-314,共3页Journal of Aerospace Power

摘　　要：本文采用有限体积法进行空间离散,Runge-Kutta法进行时间推进的办法,通过求解Euler方程来模拟二元收敛—扩散喷管跨音速流场。运用隐式残差平均技术和当地时间步长法加速计算收敛。为了消除气流参数的波动和激波前后的振荡,在方程中添加了自适应耗散项。在100个时间步以内便可获得稳态解。计算结果与试验数据和其他数值方法吻合良好。This paper presents a method for simulation of transonic flow fields in a planar nozzle. For this purpose, the Jumeson-type Runge-Kutta finite volume method is applied to solving Euler equation with the aid of local time stepping and impicit residuals averaging techniques. In such a manner the convergence rate is sped up in planar nozzle flow solution, so that the steady state can be obtained in less than a hundred iterations. An adaptive dissipation term is added to the equations to eliminate the fluctuation of the flow parameters and the vibrations in front of and behind the shock. The results of the calculations are in good agreement with the test data and the results of calculations with other numerical methods.

关 键 词：二元喷管 跨音速流动 激波 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]