论文部分内容阅读
本文提出了一个已知激波形状的情况下计算跨声速叶栅流场的方法,通道中只有一道激波并且激波后的气流速度低于声速。对超声区和亚声区分开进行计算,两区连接处满足激波关系.典型算例表明,本方法能迅速而精确地决定整个叶栅流场,得到的压力系数和唯一进气角都较好地符合实验值。计算结果不只提供了整个流场的流线分布和马氏数分布,并且还提供各流线上气流各参量变化的情况,特别是通过激波时的突跃变化。
In this paper, we propose a method for calculating the transonic cascade flow field with a known shock shape, with only one shock in the channel and a shock velocity less than the speed of sound. The separation between the ultrasonic and subsonic regions is calculated and the connection between the two regions satisfies the shock wave.The typical example shows that this method can quickly and accurately determine the flow field of the entire cascade and the pressure coefficient and the unique inlet angle Good to meet the experimental value. The calculation results not only provide the streamline distribution and the Martensite distribution of the whole flow field, but also provide the variation of each parameter of the airflow on each streamline, especially the change of the jump when passing the shock wave.