Abstract
SRM (Solid Rocket Motor) nozzle efficiency is calculated with the semi-analytical method. In the calculation, the losses of nozzle axisymmetric two-phase flow and boundary layer are determined with the method of numerical simulation of nozzle flow field. The nozzle chemical kinetic loss, throat erosive loss and submergence loss are predicted with SPP empirical method. The efficiency of four actual SRM nozzles is calculated. The computational results are in good agreement with the experimental results, and the deviation is less than 1%.
| Original language | English |
|---|---|
| Pages (from-to) | 9-11 |
| Number of pages | 3 |
| Journal | Guti Huojian Jishu/Journal of Solid Rocket Technology |
| Volume | 25 |
| Issue number | 4 |
| State | Published - Dec 2002 |
| Externally published | Yes |
Keywords
- Efficiency
- Nozzle
- Solid propellant rocket engine