An arrangement for an aircraft, comprising: a fuselage; a wing having a wing upper surface, a wing tip, a rear spar and a wing trailing edge; and a propulsor including at least one rotor having a rotor diameter and a rotor axis, the propulsor being mounted such that the rotor is located according to the following: longitudinally between the rear spar and the wing trailing edge measured along a wing chord line defined by a vertical plane coincident with the rotor axis; and vertically such that a lowest point of the rotor diameter is above the wing upper surface, wherein the wing is configured to deflect and curve upwardly under a wing loading of approximately l-g comprising a load resulting from aerodynamic lift forces generated by the wings in supporting the mass of the aircraft during take-off and the remainder of the flight, the deflected configuration of the wings providing reflective acoustic shielding of propulsor noise in a lateral direction, characterised in that the wing is constructed at least partially of composite materials to provide the upward curvature of the wing under the loading, and wherein the rotor is located: vertically such that a highest point of the rotor diameter is vertically lower than the wing tip, excluding wing tip devices, when the wing is deflected upwardly under the wing loading. a fuselage; a wing having a wing upper surface, a wing tip, a rear spar and a wing trailing edge; and a propulsor including at least one rotor having a rotor diameter and a rotor axis, the propulsor being mounted such that the rotor is located according to the following: longitudinally between the rear spar and the wing trailing edge measured along a wing chord line defined by a vertical plane coincident with the rotor axis; and vertically such that a lowest point of the rotor diameter is above the wing upper surface, wherein the wing is configured to deflect and curve upwardly under a wing loading of approximately l-g comprising a load resulting from aerodynamic lift forces generated by the wings in supporting the mass of the aircraft during take-off and the remainder of the flight, the deflected configuration of the wings providing reflective acoustic shielding of propulsor noise in a lateral direction, characterised in that the wing is constructed at least partially of composite materials to provide the upward curvature of the wing under the loading, and longitudinally between the rear spar and the wing trailing edge measured along a wing chord line defined by a vertical plane coincident with the rotor axis; and vertically such that a lowest point of the rotor diameter is above the wing upper surface, wherein the wing is configured to deflect and curve upwardly under a wing loading of approximately l-g comprising a load resulting from aerodynamic lift forces generated by the wings in supporting the mass of the aircraft during take-off and the remainder of the flight, the deflected configuration of the wings providing reflective acoustic shielding of propulsor noise in a lateral direction, characterised in that the wing is constructed at least partially of composite materials to provide the upward curvature of the wing under the loading, and wherein the rotor is located: vertically such that a highest point of the rotor diameter is vertically lower than the wing tip, excluding wing tip devices, when the wing is deflected upwardly under the wing loading. vertically such that a highest point of the rotor diameter is vertically lower than the wing tip, excluding wing tip devices, when the wing is deflected upwardly under the wing loading.