Consider a 2D airfoil with a chord length C = 5 m and angle of attack a = 12° flying kg in air whose density p= 1.225 and velocity V = 10 m/s. The resultant force center of pressure X cp = 2 m. The Normal (N) and Axial (A) forces are given as: m3 N=899 and A=19 Newtons. Find the following accurate to 3 decimal places.
a) Lift (L)