摘要
本文按Jameson等的思路,采用新的人工粘性项系数,建立显式多步有限面积方法,给出绕NACA0012翼型和RAE2822翼型跨音速流动的计算结果。
Based on the work of Jameson et. al, an explicit multistage finite-area method is established and the formula for coefficients of the artificial viscosity terms is suggested in analog to upwind schemes. The numerical results for NACA0012 and RAE2822 airfoils show that for the proposed method, effective capture of shock waves can be obtained and the suitable values of the coefficient of the added viscosity term don't have to be changed from case to case.
出处
《空气动力学学报》
CSCD
北大核心
1989年第1期26-34,共9页
Acta Aerodynamica Sinica
关键词
空气动力学
跨音速流
激波
computational aerodynamics
transonic flow
shock wave
