摘要
本文从Euler方程出发,利用LU-ADI格式对绕二元振动翼型跨声速流场进行了数值模拟。文章中给出了绕NACA0012和NACA 64A 010翼型不同状态的几组数值结果,在同某些实验和其它文献结果基本吻合的前提下,研究了振动对翼型表面压力、激波位置的非定常效应以及其它振动参数对流场非定常效应的影响。
The dynamic process is numerically simulated on two-dimensional airfoils oscillating sinusoidally. The Euler equations are required to solve with the implicit factored finite difference algorithm (LU-ADI). In this paper, numerical results of NACA0012 and NACA-64A010 airfoils are presented, some of them agree with experimental data and the results of reference[4]. By the numerical simulation, some unsteady effects are investigated.
出处
《空气动力学学报》
CSCD
北大核心
1992年第1期111-116,共6页
Acta Aerodynamica Sinica
关键词
振动翼
非定常效应
激波
数值模拟
oscillating airfoil, unsteady effect, shock wave, numerical simulation.
