摘要
采用数值模拟的方法并经过风洞实验验证分析了超音速下无翼式布局火箭弹模型俯仰气动特性随头部形状和尾舵面积的变化规律,得出在头部长细比固定不变的条件下选用单锥型弹头较双锥形弹头有更好的稳定性;选用面积大的尾舵具有更好的法向过载和稳定性;为无翼式布局弹箭气动设计提供了依据。
Numerical simulation and wind tunnel test of wingless rocket model with different heads and conclusion, wingless rocket with single conical nose condition of fixed slenderness ratio, and wingless performance of overload and stability, which provides are used to analysis pitch aerodynamic characteristics tail rudder area under supersonic condition. In a has better stability than double conical nose in the rocket with bigger tail rudder area has a better the guildance of aerodynamic configuration layout for wingless missile.
出处
《兵器装备工程学报》
CAS
2017年第5期56-60,共5页
Journal of Ordnance Equipment Engineering
关键词
无翼式布局弹箭
头部形状
尾舵面积
气动特性
wingless type
missile
nose shape
tail rudder area
aerodynamic characteristic
