Abstract
Using k-ε turbulence model and one step eddy-dissipation model, numerical studies on the reacting flow field of solid rocket ramjet with secondary air inlets were carried out. Influence of mass flow ratio on combustion efficiency and temperature field was analyzed. Numerical results show that combustion efficiency increases with a proper mass flow rate ratio, and temperature field is of benefit to thermal protection.
| Original language | English |
|---|---|
| Pages (from-to) | 401-403 |
| Number of pages | 3 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 26 |
| Issue number | 5 |
| State | Published - Oct 2005 |
Keywords
- Combustion efficiency
- Numerical simulation
- Secondary air inlet
- Solid rocket ramjet