飞机不同攻角下近场飞行绕流场数值模拟  

Numerical Simulation of Aircraft Flying in Near Field at Different Angles of Attack

作　　者：周鹏宇 柳文林 贺俊 王栋 谢名飞 李洋 ZHOU Pengyu;LIU Wenlin;HE Jun;WANG Dong;XIE Mingfei;LI Yang(Naval Aviation University,Yantai 264001,China;The No.92326 th Troop of PLA,Zhanjiang 524005,China;The No.92236 th Troop of PLA,Zhanjiang 524005,China;The No.94831 st Troop of PLA,Nanping 354300,China;The No.95172 nd of PLA,Changsha 410000,China)

机构地区：[1]海军航空大学,山东烟台264001 [2]92326部队,广东湛江524005 [3]92236部队,广东湛江524005 [4]94831部队,福建南平354300 [5]95172部队,长沙410000

出　　处：《兵器装备工程学报》2021年第8期51-57,共7页Journal of Ordnance Equipment Engineering

基　　金：国家自然科学基金项目(51375490);国家社会科学基金项目(16GJ002010)。

摘　　要：为分析飞机起降地面滑行阶段不同姿态下尾流场分布及对放减速伞的影响,以国外某飞机为研究对象,基于Delaunay非结构网格划分方法,采用RANS方程、可实现k-ε湍流模型和Roe离散格式,以及耦合隐式算法对不同速度和攻角下的飞机尾流场进行数值仿真。仿真结果表明:在该型飞机以不同速度和攻角条件下滑行时,尾部流场存在一定的反压区,表压在-320~1140 Pa,反压区大小与速度、攻角相关性不大,对放伞影响作用较小可忽略。In order to analyze the distribution of the wake field under different attitudes during the take-off and landing of the aircraft during the taxiing phase and the influence on the release of the parachute,taking a foreign aircraft as the research object,this paper used computational fluid dynamics(CFD)technology based on the Delaunay unstructured meshing method.It used RANS equation,realizable k-εturbulence model and Roe discretization scheme,and used a coupled implicit algorithm to perform numerical simulation calculations on the aircraft tail flow field at different speeds and angles of attack.The analysis of the simulation results shows that when the aircraft is gliding at different speeds and angles of attack,there is a certain back pressure zone in the tail flow field,and the gauge pressure ranges from-320 to 1140 Pa.The size of the back pressure zone is correlated with speed and angle of attack.It is not large,and the effect on the parachute deployment is small and can be ignored.

关 键 词：飞机 攻角 尾流场 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]