The two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.

摘要对一实验加热式发动机二维轴对称亚跨超音速流动进行了拟，所采用的方法是矢量分裂算法。

An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.

该文在原有加热发动机基础上进行改进，设计了覆盖发动机阳极的环形空腔，形成再生冷却道。