Consider a rectangular wing with span b = 15 m and chord c = 1,77 m, flying horizontally in steady atmosphere with velocity U∞ = 50 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 = 0,73, B = 2,53, and C = 14,27 are dimensionless constants, and Γo = 17,7 m²/s. You are asked to compute, for this wing, the global lift L in [N]:

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