Find the aerodynamic center and the CP of RAF 15 aerofoil. The chord is \(1.8 \mathrm{~m}\). Its aerofoil data are in the table below, and its \(C_{M, A C}=-0.06\). Use the pitching moment about the TRAILING edge at AoA \(=4^{\circ}\left(C_{L}=0.46, C_{D}=0.02\right.\), and \(C_{M_{-} T E}=0.27\), and draw a diagram to show the forces and the distances from the forces to \(A C, C P\).)