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 defining a fan tip radius at the fan face; wherein a downstream blockage ratio is defined as: the ⁢ ⁢ turbine ⁢ ⁢ diameter ⁢ ⁢ at ⁢ ⁢ an ⁢ ⁢ axial ⁢ ⁢ location of ⁢ ⁢ the ⁢ ⁢ lowest ⁢ ⁢ pressure ⁢ ⁢ rotor ⁢ ⁢ stage a ⁢ ⁢ distance ⁢ ⁢ f ⁢ rom ⁢ ⁢ a ⁢ ⁢ ground ⁢ ⁢ plane ⁢ ⁢ to ⁢ ⁢ the ⁢ ⁢ wing ⁢ and wherein an engine blockage ratio of: ( 2 × the fan tip radius/the engine length ) the ⁢ ⁢ downstream ⁢ ⁢ blockage ⁢ ⁢ ratio is in the range from 2.5 to 4.