大多数飞行状态都要求保持侧滑角等于零。

In most flight conditions it is desired to maintain the sideslip Angle equal to zero.

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可用来计算有攻角、侧滑角、滚转角的非对称体的气动特性。

The methods are devoted to determining aerodynamic performances for asymmetrical body with Angle of attack, Angle of side slip and roll Angle.

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但是进气道内气流分离的区域和出口截面流场畸变指数却与侧滑角的大小密切相关。

But the regions of local flow separation and distortion factor of the flow at the exit section are relevant closely to the yaw angle.

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