基于Wagner函数的卷弧翼非定常气动力分析  

Unsteady Aerodynamic Analysis of Wrap Around Wing Based on Wagner Function

作　　者：张磊[1] 高敏 周布奎 章毅 ZHANG Lei;GAO Min;ZHOU Bu-kui;ZHANG Yi(Military Academy of Sciences,Beijing 100000,China;Army Engineering University of PLA,Shijiazhuang Hebei 050003,China)

机构地区：[1]军事科学院,北京100000 [2]陆军工程大学,河北石家庄050003

出　　处：《计算机仿真》2020年第4期52-56,共5页Computer Simulation

摘　　要：为研究卷弧式尾翼的气弹特性,基于Wagner函数,建立了卷弧尾翼在非定常气动条件下的升力及滚转力矩模型。以此为基础,针对在特定振荡频率的攻角激励作用下,不同张开角度、弦长及分布数量翼片的升力,不同安装及滚转方向翼片的滚转力矩,进行了数值仿真分析,并利用fluent仿真软件进行了建模仿真验证。结果表明升力响应幅值随着张开角及弦长的增大单调递增,不同分布数量尾翼的升力近似相等,反装反旋安装方式有效降低了尾翼滚转力矩。对于卷弧尾翼弹箭的优化设计,颤振特性分析以及锥形运动的抑制等问题具有积极意义。In order to study the aeroelastic characteristics of the WAF, the lift and roll torque models of the WAF under unsteady aerodynamic conditions were established based on Wagner function. On this basis, numerical simulation analysis was carried out for the lift of WAF with different opening angles, chord lengths and distributed numbers, the roll torque of WAF with different installation and rolling direction, under the action of a specific frequency of attack angle excitation. The modeling and simulation validation was carried out by using simulation software. The results show that the lift response amplitude increases monotonously with the increase of the opening angle and the chord length, the lift of the fins with different distributions is approximately equal, and the anti-spin mounting method reduces the rolling torque of the tail fin effectively. It is of great significance to the optimization design, the analysis of flutter characteristics and the suppression of conical motion of the WAF projectile.

关 键 词：卷弧尾翼 非定常气动力 数值分析 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]