为了测量卷折尾翼细长导弹的气动力系数,进行了风洞试验,试验马赫数从0.3至3.03。导弹的外形变量包括:尾翼的几何特性参数,弹体头部外形参数和弹体尾部几何参数。同时还进行了水盘模拟试验和飞行试验,以补充风洞试验结果。其结果表明,安置尾翼的翼槽区域的气流呈“开放”状态流动。在做飞行试验时,对翼槽的形状做了修改。飞行试验中观测到导弹的射程增加,这说明通过修改翼槽形状可以大大减小气动阻力。 Wind tunnel tests were carried out to measure the aerodynamic coefficients of the rolling-tail slender missile with test Mach numbers ranging from 0.3 to 3.03. Missile profile variables include: geometric parameters of the tail fin, projectile head shape parameters and tail geometry parameters. At the same time also conducted a water tray simulation test and flight test to supplement the wind tunnel test results. The results show that the air flow in the wing region where the tail is seated is in an “open” state. In doing the flight test, the shape of the wing groove has been modified. The increase in the range of missiles observed in flight tests indicates that aerodynamic drag can be greatly reduced by modifying the shape of the wing slots.