As examples, an quasi-one-dimensional nozzle flow with shock and the subsonic and transonic flow about NACA-0012 and NACA64A-10 airfoils are calculated. The results are compared with the experimental data and the other computed results.

• 文中分别对一维管流,二维绕NACA-0012和NACA64A-10翼型在亚声速和超声速来流的跨声速流场进行了计算,并将所得结果与有关实验和计算结果进行了比较,均符合良好。