The Dutch roll motion of the aircraft is described by following relationship $\left[\begin{array}{c}\Delta \dot{\beta} \\ \Delta \dot{\mathrm{r}}\end{array}\right]=\left[\begin{array}{cc}-0.26 & -1 \\ 4.49 & -0.76\end{array}\right]\left[\begin{array}{c}\Delta \beta \\ \Delta r\end{array}\right]$ The undamped natural frequency $(\mathrm{rad} / \mathrm{s})$ and damping ratio for the Dutch roll motion in that order are:

(A) 4.68,1.02

(B) 4.49,1.02

(C) 2.165,0.235

(D) 2.165,1.02

The Dutch roll motion of the aircraft is described by following relationship $\left[\begin{array}{c}\Delta \dot{\beta} \\ \Delta \dot{\mathrm{r}}\end{array}\right]=\left[\begin{array}{cc}-0.26 & -1 \\ 4.49 & -0.76\end{array}\right]\left[\begin{array}{c}\Delta \beta \\ \Delta r\end{array}\right]$ The undamped natural frequency $(\mathrm{rad} / \mathrm{s})$ and damping ratio for the Dutch roll motion in that order are:

(A) 4.68,1.02

(B) 4.49,1.02

(C) 2.165,0.235

(D) 2.165,1.02

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