摘要
为了研究转速对弧形尾翼弹箭气动特性的影响,基于三维非定常N-S方程和滑移网格技术,对弧形尾翼弹箭的气动特性进行了数值模拟,给出了转速对弧形尾翼弹箭的影响规律,并且首次对滚转换向现象的产生机理进行了详细阐述。结果表明:在Ma=1.2~1.5时出现了滚转换向现象;随着转速的增大,其平均滚转力矩系数呈定比例减小趋势;在有攻角情况下,上下尾翼凹凸面的压力差的变化是产生2次滚转换向的主要原因。
In order to study the effect of rotational speed on aerodynamic characteristics of curved tail projectiles,this paper performs a numerical simulation of the aerodynamic characteristics of curved tail projectiles based on unsteady three-dimensional N-S equations and sliding grid technology.The influence law of rotational speed on curved tail projectile is given,and,for the first time,the generation mechanism of roll conversion to apparent phenomenon is expounded in detail.The results show that the roll conversion to apparent phenomenon occurs when Ma is within 1.2 to 1.5.As the speed increases,the average rolling moment coefficient decreases with a certain proportion.Under the condition of attack angles,the change of pressure difference on the concave and convex surfaces of the upper and lower tail fins is the main reason for the two roll moment conversion.
作者
张超
杨文风
孙鑫
王学德
ZHANG Chao;YANG Wenfeng;SUN Xin;WANG Xuede(Aircraft Institute,Chinese Flight Test Establishment,Xi’an 710089,China;Army Aviation Test Flight Battalion,Jingdezhen 333001,China;Nanjing University of Science and Technology,Nanjing 210094,China)
出处
《兵器装备工程学报》
CAS
CSCD
北大核心
2023年第4期33-38,共6页
Journal of Ordnance Equipment Engineering
基金
江苏省青蓝资助项目
国家留学基金委出国留学资助项目。
关键词
弧形尾翼
滑移网格
气动特性
数值仿真
滚转换向
curved tail
sliding grid
aerodynamic characteristics
numerical simulation
roll moment conversion
