Consider a rectangular wing with span b = 31,3 m and chord c = 1,49 m, flying horizontally in steady atmosphere with velocity U∞ = 73 m/s, and air density ρ = 1.225 kg/m3. We can assume that Re >> 1, M << 1, and that we know the circulation distribution along the wing Γ(y):

where A = 0,63, B = 3,75, and C = 16,6 are dimensionless constants, and Γo = 29,3 m²/s. You are asked to compute, for this wing, the global induced drag Di in [N]:

Note: For the computed results, provide at least 6 decimals, and use the coma "," as decimal separator.