期刊名称：International Journal of Innovative Research in Science, Engineering and Technology
印刷版ISSN：2347-6710
电子版ISSN：2319-8753
出版年度：2018
卷号：7
期号：6
页码：7476-7483
DOI：10.15680/IJIRSET.2018.0706118
出版社：S&S Publications
摘要：A nozzle is a double-conical shaped tubular structure with varying cross-sectional area. It converts the
pressure energy of the fluid flow into the kinetic energy. In a nozzle, especially de Laval or Convergent-Divergent (CD)
nozzle, the flow initially converges in the converging section of the nozzle to the throat area or minimum area, and
then then expands through the divergent section of the nozzle. Because of high kinetic energy of the exhaust gases or
flow in the exit region, the flow exits off the nozzle at a very high velocity, which in turn produces substantial thrust to
propel the rocket. But during the energy conversion, i.e., from pressure energy to kinetic energy, some part of energy is
lost. In order to achieve highest possible exit velocity and thus maximum thrust, loss should be minimized through
optimization of nozzle shape and size. In this research, multi-divergent angle in divergent portion of the nozzle is taken
in consideration for constant nozzle length and cross-sectional exit area. A computational fluid dynamics analysis has
been carried out on such nozzle for multiple cases like single divergent angle, double divergent angle, and triple
divergent angle. On comparison of the result it is observed that triple divergent angle in a nozzle produces maximum
thrust.
关键词：Convergent;divergent nozzle; de Laval nozzle; converging section; diverging section
