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。
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；
Numerical solutions agree with supersonic linearized potential flow theory as a special case when the mean angle of attack tends to zero and with piston theory in hypersonic case.
作为平均迎角趋于零的特殊情况，本文的数值结果与超声速线化的位流理论是一致的，在高超声速情况与活塞理论一致。
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