| 摘要 |
A rocket nozzle having an inlet (10), a middle region (20), a throat (30) an d an outlet, wherein a ratio of the cross-sectional area of the inlet to the throat is about 1.1. The middle region preferably has a shape which rises to an apex. Such a configuration places particles resulting from combustion on a trajectory which misses the wall of the nozzle at the throat or choke point, thereby decreasing throat erosion/ablation.
|
