NACELLE FOR GAS TURBINE ENGINE AND AIRCRAFT COMPRISING THE SAME

A nacelle (100) for housing a fan within a gas turbine engine (10) having a longitudinal centre line (101) includes a leading edge (108) and a trailing edge (110). A nacelle length (L) is defined as an axial distance between the leading edge (108) and the trailing edge (110). An azimuthal angle (θ) is defined about the longitudinal centre line (101). The nacelle length (L) varies azimuthally. The nacelle length (L) decreases azimuthally from an inboard end (116) of the nacelle (100) to an outboard end (118) of the nacelle (100).