Nozzle arrangement for a gas turbine engine

A gas turbine engine comprising:

• a bypass duct having a bypass nozzle;
• an engine core having a core nozzle;
• a pylon which is attached to the wing or airframe of an aircraft;
• a mixer fairing defining a mixer duct having a mixer duct inlet and a mixer nozzle, the mixer fairing is movably mounted to mounting rails on each side of the pylon;
• and
• a tail cone, wherein
• the mixer duct is arranged to receive an airflow from the bypass duct through the mixer duct inlet and an airflow from the engine core, when in use, and a geometry of the mixer duct is selectively adjustable by moving the mixer fairing relative to the bypass duct and engine core in use,
• the mixer fairing is movable by a first amount between a first mixer fairing position and a second mixer fairing position which simultaneously alters one or more of:
• an output flow area of the bypass nozzle, an output flow area of the mixer nozzle, and, a throat area of the mixer duct inlet, such that the respective in use airflows are altered, and
• the tail cone is movable by a second amount, different than the first amount, between a first tail cone position and a second tail cone position.