本方法可以用来计算机翼因偏航与侧滑振动而引起的滚转力矩气动导数。
This method can be applied to calculate rolling-moment derivatives of wing due to yaw and sideslip.
对具有中等后掠角机翼的飞机，产生机翼摇晃的主要原因是滚转阻尼力矩随迎角和侧滑角的变化。
For the aircraft with moderate swept wing, the main reasons of causing wing rock are the variations of roll damping moment with the Angle of attack and the sideslip Angle.
建立了带柔性后缘自适应机翼模型和带刚性偏转后缘的传统机翼模型，从升阻特性和力矩特性以及操纵效率对它们进行了比较研究。
This paper aims at presenting an investigation into aerodynamics and control reversal characteristics of adaptive wings with seamless, variable camber, flexible trailing edge.
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