Patent ID: 9718534
Date: 2017-08-01
CPC Classifications: B64C

Claim:
1. An aircraft comprising: a fuselage of a tubular shape with frontal and rear ends having a variable cross-sectional area, a wing attached to the central part of the fuselage and at least a lifting surface attached to one of the fuselage rear end and the fuselage frontal end, wherein said lifting surface is configured with a sweep angle formed between an aircraft plane of symmetry and a projection line formed by reference points located at 25% of a local chord length of the lifting surface on a plane perpendicular to the aircraft plane of symmetry, and wherein the sweep angle in an inboard part of the lifting surface comprises a variable sweep angle α and wherein the sweep angle in an outboard part of the lifting surface comprises a constant sweep angle α and wherein the lifting surface is attached to the fuselage rear end; the variable sweep angle α in the inboard part of the lifting surface is lower along its span than the constant sweep angle α