飞机地面滑行阶段尾部流场数值仿真  

Numerical Simulation of Aircraft Tail Flow Field During Ground Taxiing

作　　者：周鹏宇 李本威 贾忠湖 王强 雷勇强 Zhou Pengyu;Li Benwei;Jia Zhonghu;Wang Qiang;Lei Yongqiang(College of Aviation Foundation,Navy Aviation University,Yantai 264001,China;No.92326 Unit of PLA,Zhanjiang 524005,China;China Aerodynamics Research&Development Center,Mianyang 621000,China)

机构地区：[1]海军航空大学航空基础学院,山东烟台264001 [2]中国人民解放军92326部队,广东湛江524005 [3]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《兵工自动化》2021年第5期78-83,共6页Ordnance Industry Automation

基　　金：国家自然科学基金(51505492);泰山学者建设工程专项经费。

摘　　要：为分析飞机起降地面滑行阶段尾部流场分布情况,以计算流体力学(computational fluid dynamics,CFD)为基础,以国外某高速飞机数模为研究对象,基于Delaunay非结构三角化网格划分方法,采用3维雷诺平均N-S方程、Realizable k-ε湍流模型和Roe离散格式,运用耦合隐式算法对全机外流场进行数值模拟。以7°迎角滑行且考虑地面效应和尾喷流的情况下,对尾部压强场、温度场和速度场进行分析。结果表明,尾流场压强在轴向和横向呈下降趋势,温度和速度在轴向呈下降趋势、在横向呈双峰趋势。In order to analyze the distribution of the tail flow field during the take-off and landing ground taxiing phase,based on computational fluid dynamics(CFD),a foreign high-speed aircraft numerical model was studied,based on Delaunay unstructured triangulation mesh generation method,3D Reynolds averaged N-S equation,Realizable k-εturbulence model and ROE discrete scheme are used to simulate the external flow field of the whole aircraft by coupling hide alorithm.The tail pressure field,temperature field and velocity field are analyzed under the condition of sliding at 7°angle of attack and considering the ground effect and tail jet.The results show that the pressure in the wake decreases in the axial and transverse directions,while the temperature and velocity decrease in the axial direction and double peak in the transverse direction.

关 键 词：尾流场 地面效应 尾喷流 网格划分 数值仿真 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]