现代防御技术2017，Vol.45Issue(4)：44-49,58,7.DOI:10.3969/j.issn.1009-086x.2017.04.008
弹体前缘圆孔凹槽有/无喷射流机理研究
Flow Mechanism of Missile Body Front Round Column Grooves with/without Jet Flow
郑日升 1张庆兵 1肖志河 2刘恒军 1戚开南2
作者信息
- 1. 北京电子工程总体研究所,北京100854
- 2. 电磁散射重点实验室,北京100854
- 折叠
摘要
Abstract
To study the flow mechanism of the different diameters of round column grooves with/without jet flow,a numerical simulation method with the standard k-w SST turbulence model is used.The flow mechanism analysis is based on different round column groove diameters with/without jet.Results show that expansion wave and compression wave are formed on the edge of the round column groove.Vortex structure may exist in a round column groove.Sound velocity radial distance increases with wall surface when the round column groove diameter increases gradually.Static pressure gradually reduced in the round column groove along with the increase of angle of attack.Shock wave is generated in the grooves outlet with the increase of round column groove jet speed.Shock wave of groove outlet strength significantly increases and static pressure in round column groove decreases when the flow velocity is 600 m/s.关键词
圆孔凹槽/喷射流/湍流模型/附面层/激波/涡系结构Key words
column groove/jet flow/turbulence model/boundary layer/shock wave/vortex structure分类
军事科技引用本文复制引用
郑日升,张庆兵,肖志河,刘恒军,戚开南..弹体前缘圆孔凹槽有/无喷射流机理研究[J].现代防御技术,2017,45(4):44-49,58,7.
