摘要
The influence of mass flux of oxidizer on surface heat flux and regression rate of nitriac/HTPB propellant fuel in hybrid rocket motors was studied by means of numerical simulations method. The results show that average convective heat flux density, total heat flux density and regression rate along the axial direction are approximately proportional to the nth power of mass flux of oxidizer, and n is between 0.6~0.7. Radiant heat flux is proportional to mass flux of oxidizer. The ratio of radiant heat flux to total heat flux density increases but the increasing amplitude decreases gradually with higher mass flux of oxidizer.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 383-387 |
| 页数 | 5 |
| 期刊 | Guti Huojian Jishu/Journal of Solid Rocket Technology |
| 卷 | 32 |
| 期 | 4 |
| 出版状态 | 已出版 - 8月 2009 |