摘要
通过计算喷管二维两相流和边界层比冲损失,研究了喷管扩散段型面对其性能的影响。研究结果表明:在喷管扩散段长度一定的情况下,膨胀比有一最佳值,超过该值,喷管性能反而下降;在膨胀比一定的情况下,在一定长度范围内喷管越长,其性能越高。从而得出,为使综合性能达到最佳,在一定膨胀比下喷管扩散段长度应取喷管出口直径的1～1.25倍。该结论可供设计人员参考。
The effects of the nozzle divergent cone contour on motor performance were studied through calculating the specific impulse losses of nozzle axisymmetric two-phase flow and boundary layer. The results show when the length of nozzle divergent cone is constant, the nozzle expansion ratio has an optimum value and when the nozzle expansion ratio is a constant, nozzle performance increases along with increased length of nozzle divergent cone. It is concluded that for making the combined performance optimum, a ratio 1-1.25 of the nozzle divergent cone length to its exit diameter is reasonable. The conclusion can be referred by nozzle designers.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2004年第1期9-11,共3页
Journal of Solid Rocket Technology
基金
国防科技重点实验室基金试点项目(98JS60.2.3ZS6005)。
关键词
喷管型面
固体发动机
扩散段
两相流
真空比冲
Boundary layers
Calculations
Design
Nozzles
Performance
Solid propellants
Two phase flow
