Abstract
10 nozzles from 3 typical types are chosen under experimental tests. The results show that all nozzles can augment the thrust of baseline pulse detonation engine (PDE) and there is an optimal nozzle area ratio where thrust augmentation is maximized. Amongst all tested nozzles, the maximal augmentation of 24% is attained by a convergent-divergent nozzle. Moreover, it is validated that fill-fraction has little effect on thrust augmentation.
| Original language | English |
|---|---|
| Pages (from-to) | 869-872 |
| Number of pages | 4 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 22 |
| Issue number | 6 |
| State | Published - Jun 2007 |
Keywords
- Aerospace propulsion system
- Experimental study
- Nozzle
- Pulse detonation engine (PDE)
- Thrust augmentation