摘要
对前张式尾翼弹的气动特性研究,可以为该弹气动外形的改进和稳定装置的优化提供依据,对外弹道的解算提供前提条件。应用流体力学软件FLUENT模拟前张式尾翼弹在不同攻角和马赫数下的空气动力,分析弹丸周围的流场特性。研究表明,阻力系数和升力系数均随马赫数的增长先增大后减小,不同的是升力系数在跨音速时突然减小;阻力系数和升力系数与攻角呈正比关系;尾翼部分提供升力占总升力28%~65%,所受阻力占总阻力10%~30%。
The research on the aerodynamic characteristics of the open-tail shell can provide the prerequisite for the improvement of the aerodynamic shape and the optimization of the stabilizing device and the calculation of the external trajectory. The aerodynamic force of the tail bomb at different angles of attack and Mach number was simulated by FLUENT soft- ware. The flow field around the projectile was analyzed. The results show that the drag coef- ficient and the lift coefficient both increase and decrease with the increase of the Mach num- ber. The difference is that the lift coefficient decreases abruptly at transonic velocity. The drag coefficient and lift coefficient are proportional to the angle of attack. Lift part of the lift to the total lift of 28% to 65% .subiect to resistance to the total resistance of 10% to 30%.
出处
《沈阳理工大学学报》
CAS
2017年第6期26-30,共5页
Journal of Shenyang Ligong University
关键词
前张式尾翼弹
攻角
气动特性
open-tail shell
angle of attack
aerodynamic characteristics
作者简介
焦志刚（1963-），男，教授，研究方向：弹药工程。
