An aircraft is flying at sea level with a velocity of 260 m/s, if we consider its wing as a rectangular flat plate of span 10.0m and chord 2.0m, calculate the boundary layer thickness at the wing trailing edge and total skin friction drag for: (density = 1.225 kg/m3, dynamic viscosity = 1.8 x 10-5 kg/ms, assume that the flow is incompressible). (i) completely laminar flow (ii) completely turbulent flow