摘要
基于有限体积法计算了一种具有小长径比、大展弦比张开式尾翼弹在有攻角超声速粘性流动时的气动特性,分析了该弹周围的流场特性。研究结果表明,该尾翼弹的阻力系数和升力系数均随着马赫数增大而减少,随攻角增大而增大,且呈线性变化;当马赫数从2增大到4时,攻角从4°增大到12°,压心位置变化范围占全弹长的10.3%。
By using the finite volume method, this paper calculates the aerodynamic characteristics of the flip-out open-tail shell with the small length-diameter ratio and large aspect ratio in supersonic viscous flow when attack angles exist. The characteristics of the flow field around the shell are and are all in the linearity rule. The change range of the pressure center position is 10.3% of the total shell length when the Mach number increases from 2 to 4 and the attack angle from 4°to 12°.
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2014年第5期597-601,共5页
Journal of Nanjing University of Science and Technology
关键词
小长径比
大展弦比
尾翼弹
攻角
气动特性
small length-diameter ratio
large aspect ratio
open-tail shell
attack angles
aerodynamic characteristics