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(a) An aircraft has a total mass of 120kg, a wing area of 20m. It operated with an aerofoil section having CL = 1.0

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(a) An aircraft has a total mass of 120kg, a wing area of 20m. It operated with an aerofoil section having CL = 1.0 and CD=0.01. Assuming that the total drag of the wing represents the whole drag of the aircraft, find the power input required for to overcome gravity and take off. Assume density of air to be 1.2 kg/m.

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