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

摘要对一实验电弧加热式发动机二维轴对称亚跨超音速流动进行了数值模拟，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.

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