GB643987A - Improvements in or relating to aircraft - Google Patents

Abstract

643,987. Controlling aircraft. STALKER, E. A. Oct. 16, 1946, No. 30796. Convention date, Nov. 26, 1945. [Class 4] An aircraft wing is provided with nose and tail flaps, and flap-actuating mechanism responsive to pressure difference at two spaced points on the upper surface of the wing between the flaps, whereby relative adjustment of the flaps in co-ordination is effected in response to variations in the pressure difference so as to maintain a predetermined pressure distribution over the wing surface. As shown, the invention is applied to a tailless aircraft with swept-back wings, the latter being of thick section and pronounced camber, to produce a substantially constant pressure over the major portion of the chord, as shown by the curve 86, Fig. 10, such a pressure distribution serving to reduce tip stalling due to outward airflow. The nose and tail flaps 6, 8 are hinged to the underside of the wing at points 100, 102 and the pressure control points 110, 112 on the upper wing surface are connected to bellows 118, 119 controlling a valve 120 which governs the supply of pressure fluid to a power jack 122 operating the flaps through links 104, 106. In operation movement of the tail flap 8 by the pilot modifies the pressure distribution on the wing surface, which is restored to its original form by the automatic operation of the nose flap 6. In order to reduce still further the tendency to tip stalling, the boundary layer is sucked through slots 130, 131 in the upper surface of the outboard wing portions, and discharged through slots 134, 136 in the inboard portions. The wing profile is derived from a symmetrical section, Fig. 9 (not shown), of which the leading edge portion is substantially elliptical in section.