Consider an airplane that weights 1.4×10 N and cruises in level flight at 300 km/h at an altitude with air density of 0.9 kg/m³. The wing has a surface area of 17 m² and an aspect ratio of 6.2. Assume that the lift coefficient is a linear function of the angle of attack and al-0 -1.2°. If the load distribution is elliptical, calculate the following: a) Value of the circulation in the plane of symmetry, To b) Downwash velocity, w c) Induced drag coefficient, CDi d) Effective angle of attack, eff e) Geometric angle of attack, a