Abstract: This non-limiting technology proposes to modify the maximum angle of attack setting (?setting) of the Stall Protection or Stall Warning Systems continuously or continually, according to the elapsed time since icing is first detected and/or the deicing system was activated. A changing maximum angle of attack setting maintains approximately the same angle-of-attack margin to the stall angle-of-attack by taking into account improvements in the stall angle of attack due to inflight icing removal and icing prevention by operation of an inflight deicing system. The aircraft flying with an angle of attack closer to the critical angle of attack is capable of producing a higher coefficient of lift.

Abstract: This non-limiting technology proposes to modify the maximum angle of attack setting (?setting) of the Stall Protection or Stall Warning Systems continuously or continually, according to the elapsed time since icing is first detected and/or the deicing system was activated. A changing maximum angle of attack setting maintains approximately the same angle-of-attack margin to the stall angle-of-attack by taking into account improvements in the stall angle of attack due to inflight icing removal and icing prevention by operation of an inflight deicing system. The aircraft flying with an angle of attack closer to the critical angle of attack is capable of producing a higher coefficient of lift.

Abstract: Pylon fairings for an aircraft turbojet engine mounted below an aircraft wing are provided with inboard and outboard lateral faces which converge rearwardly to form a trailing edge of the pylon fairing and which are positioned so as to contact a portion of a cold flow exiting a fan duct of the turbojet engine, and a bottom face positioned above a hot exhaust flow exiting an exhaust nozzle of the turbojet engine. The trailing edge of the pylon fairing extends in an upward direction relative to an engine longitudinal axis of symmetry between a lower terminus at the bottom face and an upper terminus located at a lower surface of the aircraft wing. The lower terminus is coincident with a longitudinal midplane of the turbojet engine, and the upper terminus is offset in an inboard direction so that the trailing edge of the pylon fairing is cambered in the inboard direction between the lower terminus and the upper terminus.

Abstract: Pylon fairings for an aircraft turbojet engine mounted below an aircraft wing are provided with inboard and outboard lateral faces which converge rearwardly to form a trailing edge of the pylon fairing and which are positioned so as to contact a portion of a cold flow exiting a fan duct of the turbojet engine, and a bottom face positioned above a hot exhaust flow exiting an exhaust nozzle of the turbojet engine. The trailing edge of the pylon fairing extends in an upward direction relative to an engine longitudinal axis of symmetry between a lower terminus at the bottom face and an upper terminus located at a lower surface of the aircraft wing. The lower terminus is coincident with a longitudinal midplane of the turbojet engine, and the upper terminus is offset in an inboard direction so that the trailing edge of the pylon fairing is cambered in the inboard direction between the lower terminus and the upper terminus.