GAS TURBINE ENGINE MOUNTED ABOVE WING AND WITH CAMBER

A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation (X). An outer nacelle (106A) surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle (106A) is formed with camber (122) so as to be curved in a first plane away from the axis of rotation (X) in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction.