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

作　　者：郑日升[1] 张庆兵[1] 肖志河 刘恒军[1] 戚开南 

机构地区：[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

出　　处：《现代防御技术》2017年第4期44-49,58,共7页Modern Defence Technology

摘　　要：为了研究不同圆孔凹槽直径及有/无喷射流流动机理,采用标准的k-w SST湍流模型数值计算方法进行分析。结果表明:当流体经过圆孔凹槽时,在圆孔凹槽边缘会形成膨胀波和压缩波,在圆孔凹槽内可能会形成涡流结构,并保持低速流体。当圆孔凹槽直径逐渐增加时,引起弹体壁面声速径向距离增加。同时,随着攻角的增大,圆孔凹槽内的静压逐渐降低;圆孔凹槽喷流速度的增加导致凹槽出口会出现激波现象,当喷流速度达到600 m/s时,凹槽出口激波强度明显增加,圆孔凹槽内静压减小。To study the flow mechanism of the different diameters of round column grooves with/with- out 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. Vor- tex structure may exist in a round column groove. Sound velocity radial distance increases with wall sur- face 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 signifi- cantly 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 

分 类 号：TJ760[兵器科学与技术—武器系统与运用工程]