Patent ID: 8523101

Claim:
An aircraft comprising: a fuselage; at least one wing secured to the fuselage; a front horizontal stabilizer secured to the fuselage on a side of a front end of the fuselage with respect to the wing according to a longitudinal axis X of the aircraft; at least first and second propulsion jet engines; wherein the at least first and second propulsion jet engines are arranged side by side inside a stationary structure of a propulsion assembly, the propulsion assembly located on a top of the fuselage, said stationary structure forming one part with a structure of the fuselage, and such that rear outlets of the stationary structure are proximate a rear end of the fuselage; a fuselage high lift flap device arranged at the rear end of the fuselage, and comprising at least one fuselage high lift flap configured to adopt a first position wherein the at least one fuselage high lift flap is located substantially horizontal with respect to reference axes of the aircraft and extending beyond the rear outlets in the longitudinal direction of the aircraft, and to adopt at least a second position, wherein the at least one fuselage high lift flap is deflected downward with respect to the first position; wherein the stationary structure comprising the at least first and second propulsion jet engines and the fuselage high lift flap device are arranged on the fuselage such that the engines blow air along a top skin of the at least one fuselage high lift flap; and wherein the at least one fuselage high lift flap has at least one position wherein said at least one fuselage high lift flap is totally or partially retracted in an interior space of the rear part of the fuselage.