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研究了亚音速下弹丸尾锥形状对飞行稳定性的影响。试验研究证明，在尾锥长度小于一倍口径的条件下，尾锥的折转变化对空气动力会产生显著影响，尾锥长度的极限值为０．８７ｄ。这一结果可供弹丸设计或从事相关工作的工程技术人员参考。
The effect of subsonic cone tail shape on flight stability at sub-sonic velocity was investigated. Experimental studies have shown that under the condition that the length of tail cone is less than one time, the change of tail cone has a significant effect on aerodynamics, and the limit value of tail length is 0.87d. This result can be used for projectile design or related work of engineering and technical personnel for reference.