A vertical take-off and landing (VTOL) aircraft comprising: a fuselage defining a forward end and an aft end, the fuselage accommodating at least one engine; a left wing and a right wing extending from either side of the fuselage; a lift fan drive system accommodated within each wing (18, 20); a forward thrust fan drive system fitted proximate the aft end of the fuselage; and a stabiliser arrangement proximate the forward thrust fan drive system, wherein each wing (18, 20) comprises a rotor housing portion (18.1, 20.1) extending away from the fuselage and a wing tip portion (18.2, 20.2) extending away from the rotor housing portion (18.1, 20.1), the wing tip portion (18.2, 20.2) being angled towards the rear and side of the aircraft, wherein each rotor housing portion (18.1, 20.1) accommodates a lift fan (28.1, 28.2; 28.3, 28.4) with variable pitch blades, the lift fan (28.1, 28.2; 28.3, 28.4) forming part of the lift fan drive system, wherein the aircraft comprises a stability system having a plurality of inputs, including that of a pilot, and a plurality of actuating outputs, wherein a lower opening of each rotor housing portion (18.1, 20.1) is fitted with a series of louvers, the louvers being orientated and angled during flight to redirect the thrust generated by the lift fans (28.1, 28.2; 28.3, 28.4), wherein the fuselage comprises multiple turbine engines, with power being transferred from each of the engines to each of the lift fans (28.1, 28.2; 28.3, 28.4) of the lift fan drive systems through a single planetary gearbox, the multiple turbine engines also being used to power the forward thrust fan drive system through a secondary gearbox. a fuselage defining a forward end and an aft end, the fuselage accommodating at least one engine; a left wing and a right wing extending from either side of the fuselage; a lift fan drive system accommodated within each wing (18, 20); a forward thrust fan drive system fitted proximate the aft end of the fuselage; and a stabiliser arrangement proximate the forward thrust fan drive system, wherein each wing (18, 20) comprises a rotor housing portion (18.1, 20.1) extending away from the fuselage and a wing tip portion (18.2, 20.2) extending away from the rotor housing portion (18.1, 20.1), the wing tip portion (18.2, 20.2) being angled towards the rear and side of the aircraft, wherein each rotor housing portion (18.1, 20.1) accommodates a lift fan (28.1, 28.2; 28.3, 28.4) with variable pitch blades, the lift fan (28.1, 28.2; 28.3, 28.4) forming part of the lift fan drive system, wherein the aircraft comprises a stability system having a plurality of inputs, including that of a pilot, and a plurality of actuating outputs, wherein a lower opening of each rotor housing portion (18.1, 20.1) is fitted with a series of louvers, the louvers being orientated and angled during flight to redirect the thrust generated by the lift fans (28.1, 28.2; 28.3, 28.4), wherein the fuselage comprises multiple turbine engines, with power being transferred from each of the engines to each of the lift fans (28.1, 28.2; 28.3, 28.4) of the lift fan drive systems through a single planetary gearbox, the multiple turbine engines also being used to power the forward thrust fan drive system through a secondary gearbox.