The roots obtained by solving longitudinal characteristic equations of motion for a statically stable aircraft are given below:
$\lambda_{1,2}=-0.02 \pm 0.30 i, \lambda_{3,4}=-2.00 \pm 2.50 i,$ where $i=\sqrt{-1}$
The undamped short-period longitudinal natural frequency (radians/sec) and damping ratio, in that order, are close to
(A) 3.40,0.73
(B) 3.36,0.65
(C) 3.83,0.56
The roots obtained by solving longitudinal characteristic equations of motion for a statically stable aircraft are given below:
$\lambda_{1,2}=-0.02 \pm 0.30 i, \lambda_{3,4}=-2.00 \pm 2.50 i,$ where $i=\sqrt{-1}$
The undamped short-period longitudinal natural frequency (radians/sec) and damping ratio, in that order, are close to
(A) 3.40,0.73
(B) 3.36,0.65
(C) 3.83,0.56
(D) 3.20,0.63

The roots obtained by solving longitudinal characteristic equations of motion for a statically stable aircraft are given below:
$\lambda_{1,2}=-0.02 \pm 0.30 i, \lambda_{3,4}=-2.00 \pm 2.50 i,$ where $i=\sqrt{-1}$
The undamped short-period longitudinal natural frequency (radians/sec) and damping ratio, in that order, are close to
(A) 3.40,0.73
(B) 3.36,0.65
(C) 3.83,0.56
The roots obtained by solving longitudinal characteristic equations of motion for a statically stable aircraft are given below:
$\lambda_{1,2}=-0.02 \pm 0.30 i, \lambda_{3,4}=-2.00 \pm 2.50 i,$ where $i=\sqrt{-1}$
The undamped short-period longitudinal natural frequency (radians/sec) and damping ratio, in that order, are close to
(A) 3.40,0.73
(B) 3.36,0.65
(C) 3.83,0.56
(D) 3.20,0.63