This question is related to lifting line theory and Prantl's equation

An untwisted wing having an elliptic lift and chord distribution has a chord of 2 m at its centre and a span of 20 m. It has a zero-lift angle of 4 . Calculate the lift-curve slope, dCL/d, of the wing. If = 6 and the upstream velocity is 140 m/s, calculate: the circulation, 0, at the centre line, the downwash velocity and angle, the lift and lift coefficient, and the induced drag and induced-drag coefficient. What is the equivalent lift coefficient for the two-dimensional wing section?