An aircraft is flying with inertial ground and wind speeds of $\vec{v}_{g}^{b}=(100,5,5) \mathrm{m} / \mathrm{s}$ and $\vec{v}_{w}^{b}=(0,-5,-10) \mathrm{m} / \mathrm{s},$ respectively, as expressed in the body frame. The corresponding sideslip angle (in degrees) is
(A) 0
(B) 5.65
(C) 8.49
(D) 9.54
An aircraft is flying with inertial ground and wind speeds of $\vec{v}_{g}^{b}=(100,5,5) \mathrm{m} / \mathrm{s}$ and $\vec{v}_{w}^{b}=(0,-5,-10) \mathrm{m} / \mathrm{s},$ respectively, as expressed in the body frame. The corresponding sideslip angle (in degrees) is
(A) 0
(B) 5.65
(C) 8.49
(D) 9.54