Consider an aircraft with a body-fixed reference frame F, as shown in Figure 1 The velocity of point c,the aircraft's center of mass, relative to the point w with respect to F, is y/ and equal to \stackrel{v^{c w / i}}{\rightarrow}=\underset{\mathcal{F}_{b}^{T}}{\mathcal{F}_{b}^{T}}\left[\begin{array}{c}

150 \\

-20 \\

0

\end{array}\right] \mathrm{m} / \mathrm{s} The force generated by the control surfaces at the tail f is given by \stackrel{v^{e}}{\rightarrow}=\underset{\mathcal{F}^{T}}{\rightarrow b}\left[\begin{array}{c}

-200 \\

140 \\

0

\end{array}\right] \mathrm{N} 1. What is the aircraft's angle of attack a (i.e., the angle between w/ and ren)?2. What is recx f2 given that ||ec||= 10 m?→