Fan downstream guide vanes of a turbofan engine

Fan downstream guide vanes for a turbofan engine, comprising:

• the downstream guide vanes extending in one vane height between an inner and an outer sidewall in a bypass duct of the turbofan engine and whose shape is established by a plurality of aerodynamic profiles radially stacked on top of each other and determined by a skeleton line angle distribution with an appertaining, superimposed thickness distribution over a chord length
• an upper and a lower profile (1max, 2min) forming an upper limitation and a lower limitation determined by specified supporting points (St) of chord lengths of 0, 9, 14, 22, 35, 46, 60, 89 and 100%, respectively having:
• dimensionless values of a skeleton line angle (αlo) of 0, 0.2, 0.4, 0.6, 0.8, 0.9, 0.9, 0.95 and 1 and a thickness (do) of 0, 0.85, 0.95, 1, 0.95, 0.875, 0.7, 0.2 and 0 as the upper limitation of a skeleton line angle distribution and a thickness distribution (1Smax, 1Dmax);
• a skeleton line angle (αlu) of 0, 0.05, 0.1, 0.25, 0.45, 0.6, 0.725, 0.85 and 1 and a thickness (du) of 0, 0.4, 0.55, 0.75, 0.95, 1, 0.9, 0.35, and 0 as the lower limitation of the skeleton line angle distribution and the thickness distribution (2Smax, 2Dmax);
• and
• a plurality of intermediate profiles (3int) situated between the upper and the lower limitations.