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 ; 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 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 ; 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 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 . <EOS>