带扰动块的细长旋成体背部绕流数值模拟  

Numerical simulation of flow around slender body with disturbing block

作　　者：刘克奇 李国辉[1] 张浩南 张宴嘉 LIU Keqi;LI Guohui;ZHANG Haonan;ZHANG Yanjia(Aviation Operations Service Academy,Aviation University Air Force,Changchun 130000,China)

机构地区：[1]空军航空大学航空作战勤务学院,长春130000

出　　处：《北京航空航天大学学报》2021年第7期1495-1504,共10页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：为了更好地了解细长旋成体背部绕流非对称涡的形成机理,研究了头部带扰动块对细长旋成体背部绕流结构的影响,通过雷诺平均Navier-Stokes(RANS)法对细长旋成体模型在攻角5°~60°范围内进行仿真。在攻角分别为20°和30°时对是否添加扰动块模型进行对比,分析了不同截面绕流沿轴向位置的发展,提出了验证拓扑结构的一种方法,找到了各流态下奇点的位置,通过涡核位置对模型背部绕流的发展进行了分析。研究表明:添加已知规则扰动块可以加快各绕流结构间的转换速度,使非对称涡产生的攻角减小。In this paper,the influence of the head disturbance block on the structure of the flow around the back of the slender body is studied.The slender body model is simulated at the angle of attack of 5°-60°through numerical simulation.The numerical calculation method selected is the Reynolds Average Navier-Stokes(RANS)method.This paper mainly compares whether to add a disturbance block model at an angle of attack ofα=20°,30°,analyzes the development of the flow around different sections along with the axial position,proposes a method to verify the topological structure,and finds the position of the singularity in each flow state.The position of the vortex core is used to analyze the development of the flow around the back of the model.It is found that the premise of adding a known regular disturbance block can speed up the conversion speed between the surrounding flow structures,and will reduce the angle of attack generated by the asymmetric vortex.

关 键 词：绕流结构 细长旋成体 非对称流动 鞍点 拓扑结构 

分 类 号：V221[航空宇航科学与技术—飞行器设计] TJ760[兵器科学与技术—武器系统与运用工程]