Abstract: An aircraft arrangement for Mini or Micro UAV comprising a fore wing (14) and an aft wing (12) in tandem closed-coupled arrangement. The aft wing (12) has side panels (18) and control surfaces (19), and tapered planform with positive sweep, while the fore wing (14) has non-positive trailing edge sweep. The fore wing (14) and the aft wing (12) are disposed at different height, and the aircraft arrangement has no other wings or tail arrangements.

Abstract: The invention relates to an aircraft, and a method for operating an aircraft, the aircraft having a longitudinally unstable configuration and swept wings, the swept wings being based on aerofoils having a leading edge and configured for preventing attachment line transition in conditions of laminar flow over the swept wing for at least a predetermined first range of lift coefficients at a second range of Reynolds numbers. The invention also relates to an aerofoil, and to a method for providing an aerofoil, the airfoil being configured for a thick-sectioned subsonic/transonic swept wing, having a curved leading edge, a trailing edge, a thickness dimension and a chord dimension, wherein the leading edge comprises a leading edge curvature associated with a leading edge radius that is configured for preventing attachment line transition in conditions of laminar flow over the swept wing.

Abstract: The invention relates to an aircraft, and a method for operating an aircraft, the aircraft having a longitudinally unstable configuration and swept wings, the swept wings being based on aerofoils having a leading edge and configured for preventing attachment line transition in conditions of laminar flow over the swept wing for at least a predetermined first range of lift coefficients at a second range of Reynolds numbers. The invention also relates to an aerofoil, and to a method for providing an aerofoil, the airfoil being configured for a thick-sectioned subsonic/transonic swept wing, having a curved leading edge, a trailing edge, a thickness dimension and a chord dimension, wherein the leading edge comprises a leading edge curvature associated with a leading edge radius that is configured for preventing attachment line transition in conditions of laminar flow over the swept wing.