头部和尾舵布局对弹箭俯仰气动特性影响

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.

Effects of Nose Shape and Tail Rudder Area on Pitch Aerodynamic Characterics for Missile

Numerical simulation and wind tunnel test are used to analysis pitch aerodynamic characteristics of wingless rocket model with different heads and tail rudder area under supersonic condition.In a conclusion, wingless rocket with single conical nose has better stability than double conical nose in the condition of fixed slenderness ratio, and wingless rocket with bigger tail rudder area has a better performance of overload and stability.which provides the guildance of aerodynamic configuration layout for wingless missile.