| タイトル | Numerical analysis of bipropellant combustion in liquid thrust chambers by an Eulerian-Eulerian approach |
| 著者（英） | Dang, A. L.; Navaz, H. K.; Rangel, R. H. |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 1992-07-01 |
| 言語 | eng |
| 内容記述 | The liquid thrust chambers performance (LTCP) code is used for parametric studies of flow and combustion in liquid rocket engines. Multiphase flow equations are solved in an Eulerian-Eulerian framework, and multistep finite rate chemistry is incorporated. The discretization scheme is fully implicit and is based on the total variation diminishing (TVD) scheme, which is accurate, robust, very efficient and capable of handling steep gradients and stiff chemistry. Effects of injection velocity and chamber size have been considered, and the effect of group combustion on the evaporation rate has been studied for a dense spray. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 92A54139
AIAA PAPER 92-3735 |
| 権利 | Copyright |
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