A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan; wherein a downstream blockage ratio of: the ⁢ ⁢ turbine ⁢ ⁢ diameter ⁢ ⁢ at ⁢ ⁢ an ⁢ ⁢ axial location ⁢ ⁢ of ⁢ ⁢ the ⁢ ⁢ lowest ⁢ ⁢ pressure ⁢ ⁢ rotor ⁢ ⁢ stage a ⁢ ⁢ distance ⁢ ⁢ from ⁢ ⁢ a ⁢ ⁢ ground ⁢ ⁢ plane ⁢ ⁢ to ⁢ ⁢ the ⁢ ⁢ wing is in the range from 0.2 to 0.3.