The aerodynamic drag of different models at zero angle of attack in the experiment is calculated using the simplified procedure.
在零攻角实验时不同模型的空气动力阻力是采用简化方法来计算的；
A zero-install roll Angle of the wrap around fins projectile still has roll moment at zero Angle of attack.
卷弧翼与弹身扣合较好，在零攻角下会产生滚转力矩。
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