An aircraft comprising: an aircraft fuselage having a relatively wide cross-sectional area at a location adjacent to and forward of a tail wherein said relatively wide cross-section area has a width to height ratio greater than or equal to about 1.5; main gas turbine engines for driving the aircraft mounted at a location remote from said relatively wide portion of said fuselage; a cross flow fan incorporated into the aircraft fuselage and comprising: an ingestion fan rotor positioned in a tail section of the aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface; and a drive arrangement for said ingestion fan rotor, wherein said ingestion fan rotor is positioned at said wide cross-sectional area; and rear stabilizers (28, 62) extending upwardly from the fuselage and connected to the tail; wherein there is a combined propulsion provided by said ingestion fan rotor and said main gas turbine engines in combination, and said ingestion fan rotor provides greater than or equal to 10% and less than or equal to 25% of the total propulsion, characterised in that: said drive arrangement includes an ingestion gas turbine engine driving the ingestion fan rotor; and wherein said drive arrangement is mounted in at least one of said stabilizers. an aircraft fuselage having a relatively wide cross-sectional area at a location adjacent to and forward of a tail wherein said relatively wide cross-section area has a width to height ratio greater than or equal to about 1.5; main gas turbine engines for driving the aircraft mounted at a location remote from said relatively wide portion of said fuselage; a cross flow fan incorporated into the aircraft fuselage and comprising: an ingestion fan rotor positioned in a tail section of the aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface; and a drive arrangement for said ingestion fan rotor, wherein said ingestion fan rotor is positioned at said wide cross-sectional area; and rear stabilizers (28, 62) extending upwardly from the fuselage and connected to the tail; wherein there is a combined propulsion provided by said ingestion fan rotor and said main gas turbine engines in combination, and said ingestion fan rotor provides greater than or equal to 10% and less than or equal to 25% of the total propulsion, an ingestion fan rotor positioned in a tail section of the aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface; and a drive arrangement for said ingestion fan rotor, wherein said ingestion fan rotor is positioned at said wide cross-sectional area; and rear stabilizers (28, 62) extending upwardly from the fuselage and connected to the tail; wherein there is a combined propulsion provided by said ingestion fan rotor and said main gas turbine engines in combination, and said ingestion fan rotor provides greater than or equal to 10% and less than or equal to 25% of the total propulsion, characterised in that: said drive arrangement includes an ingestion gas turbine engine driving the ingestion fan rotor; and wherein said drive arrangement is mounted in at least one of said stabilizers. said drive arrangement includes an ingestion gas turbine engine driving the ingestion fan rotor; and wherein said drive arrangement is mounted in at least one of said stabilizers.