Numerical simulation on the plume flow structures for a missile

被引：0
|
作者：
Xu, Chun-Guang [1 ]
Liu, Jun [1 ]
机构：
[1] Inst. of Aerosp. and Mat. Eng., Natl. Univ. of Defence Technol., Changsha 410073, China
来源：
| 2003年 / Journal of Propulsion Technology卷 / 24期
关键词：
Combustion - Navier Stokes equations - Thermal plumes - Wakes;
D O I：
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中图分类号：
学科分类号：
摘要：
A detailed numerical investigation of a kind of missile's plume fields was simulated using an existing three dimensional TLA N-S computational technique based on ENO difference scheme for Mach number Ma=0.8-1.6, altitude H=2 km-15 km, combustor total pressure pc=20 MPa and 40 MPa. The result shows altitude and combustor total pressure markedly influence plume fields width. A formula was obtained by analyzing flows structures and measurement. The result can be used as the foundation to evaluate the edge of plume flows.
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