摘要
本文全速势方程的有限差分数值计算结果,给出了0°和2°攻角下NACA0012翼型当地马赫数分布冻结时的自由流马赫数范围,以及M_∞稍大于1变至1.30时前方脱体激波的变化位置。
The numerical finite difference computed results of the full potential equation give the range of freestream Mach numbers over which the local Mach number is frozen for NACA0012 airfoil at α=0° and α=2°, and the distances between the detached shock and airfoil leading edge at Mach numbers from 1.05 to 1.30.
出处
《空气动力学学报》
CSCD
北大核心
1989年第2期255-257,共3页
Acta Aerodynamica Sinica
