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

摘要对一实验电弧式维轴对称亚跨超音速流进行了数值模拟，所用的方法是矢通量分裂算法。

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

该文在原有电弧基础上进行改进，设计了覆盖阳极的环形空腔，形成再生冷却通道。