INTEGRAL CONFIGURATION AIRCRAFT Russian patent published in 2009 - IPC B64C1/26 B64C3/14 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering. Proposed aircraft consists of empennage, control surfaces, power plant, aircraft systems, equipment, fuselage, wing with the sweepback of leading edge of 30° to 35° and leading-edge wing extension sweepback of 60° to 70°. The section of transition from wing to fuselage is formed by a symmetric section with the thickness of 13% to 14%. The outer wings are formed by unified supercritical section with thickness making from 13% to 10% with linear section thickness variation over the wing spin. The section twist on inboard rib is negative approximating to -3°, that of the transition from leading-edge wing extension to wing spin is positive approximating to +2°. Note that the law of twist angle variation between the above sections is taken to be linear.

EFFECT: higher stability and safety.

4 dwg