摘要
本文应用分区对接网格技术 ,由于采用了对接面上网格点完全对应的方法 ,能自动满足通量守恒和计算的稳定性。采用有限体积算法下的原始变量型NND格式 ,求解NS方程 ,数值模拟了复杂外形的高超声速层流流场 。
In this paper, a multi block patched grid technique is developed. Since the grid points on the sides of an interface are one to one correspondence, the interpolation is not needed and the flux conservation as well as the numerical stability is satisfied automatically. Hypersonic laminar flows past typical complicated configurations are numerically simulated by solving NS equations with finite volume primitive variable type NND scheme. The computational results are agreed well with the experimental data.
出处
《空气动力学学报》
CSCD
北大核心
2002年第2期179-183,共5页
Acta Aerodynamica Sinica
