The chord of an airplane's thin wing is 2 m and it is flying at 200 km/h. Using the flat-plate model, calculate the displacement thickness and friction coefficient at he wing's trailing edge
(a) assuming laminar flow and
(b) assuming turbulent flow. Assume that μ = 1.8 × 10-5 N s/m2 and ρ = 1.2 kg/m3.