HIGH-LIFT FUSELAGE AIRCRAFT Russian patent published in 2009 - IPC B64C39/10 B64C1/00 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering. Proposed aircraft represents a unified (integral) 3D system made up of elliptical fuselage with the height-to-width ratio of 1:2 to 1:4, a wing with elongation λ=7 to 11 and wing taper ratio η=3-4. Proposed system lengthwise sections consist of composite sections modified so that the fuselage section and wing root sections satisfy the conditions of maximum Mk* and Mzo at moderate Cy max, and the root section satisfies the condition of Cy max maximum. The sections feature negative aerofoil section camber f~0.015 to 0.02 varying from the aircraft axis to over with wing span from X=0.6 for root section to X=0.9 nearby the wing tip section. Relative fuselage section thickness does not exceed C~0.17 and that of wind sections does not exceed C~0.15. Angles of rear surface inclination nearby rear edge of any aircraft surface does not exceed σ<6 degrees.

EFFECT: higher stability and controllability.

5 dwg