An aeroplane of 4×10^4 kg mass is designed with the line of thrust 8×10^(-1) m above the line of drag. In routine flight the drag is 15.2 kN, and the centre of pressure on the mainplane is 200 mm behind the centre of mass. If the centre of pressure on the tailplane is 12 m behind the centre of mass, what is the lift from the tailplane?