卷弧翼与弹身扣合较好，在零攻角下会产生滚转力矩。
A zero-install roll Angle of the wrap around fins projectile still has roll moment at zero Angle of attack.
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；
The aerodynamic drag of different models at zero angle of attack in the experiment is calculated using the simplified procedure.
本文研究平面强爆震波对静止的零攻角二维对称薄翼的绕射问题，并求得解析解。
An analytical solution is obtained for the diffraction of strong detonation waves by a stationary two-dimensional thin airfoil.
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