在CG-01风洞中进行了某三片弧尾翼鸭式导弹常规静态测力实验,目的是研究此旋转导弹在不同滚转角下的气动特性,通过实验获取了在马赫数0.4~2.0,攻角0°~10°以及滚转角0°~315°条件下的风洞实验结果。实验结果表明:三片弧尾翼鸭式导弹在不同滚转角下的气动特性存在一定差异,小攻角时滚转角对气动系数的影响较小,但当攻角增大后,升力系数、阻力系数、俯仰力矩系数及滚转力矩系数随滚转角的变化均会出现波动,并随着攻角的增大波动幅值逐渐加剧。

Based on static force measurement, the experiment of a canard missile with three wrap around fins was carried out in the CG-01 wind tunnel in order to study on the aerodynamic characteristics of rolling missile under different roll angle. The wind tunnel experimental results were gained at 0.4~2.0 Mach number, 0°~10° angle of attack and 0°~315° angle of roll. The experimental results indicate that the aerodynamic characteristics of canard missile with three wrap around fins exist a certain difference at different roll angle. The roll angle has slight influence on aerodynamic characteristics at low angle of attack, but when the angle of attack increases, the lift coefficient, drag coefficient, pitching moment coefficient and rolling moment coefficient all begin to fluctuate with the roll angle change, and the fluctuation amplitude of aerodynamic coefficients gradually increase with the angle of attack increase.