GB675994A - Improvements in or relating to aircraft wings - Google Patents

Abstract

675,994. Controlling aircraft. OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AERONAUTIQUES and SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU SUD-OUEST. July 30, 1948 [July 31, 1947; Dec. 22, 1947; July 17, 1948], Nos. 20370/48, 20371/48 and 20372/48. Class 4. An aircraft wing comprises a main section and two pivotal sections whereby the camber of the wing can be varied, the upper surface of said main section defining with the upper surface of one of said pivotal sections an air inlet slot which is variable as said pivotal section is moved to vary the camber of the wing, an airflow discharge slot formed at the upper rear portion of that wing section which lies between the two other sections, a spanwise directed pipe disposed between said air inlet and discharge slots, fluid ejecting means operated through said pipe, a mixing chamber establishing communication between said inlet and discharge slots, and means for supplying fluid under pressure to said ejecting means through said pipe to produce an aspirating effect by the latter for cansing a sheet of air to be drawn in through said inlet slot and discharged through said discharge slot. The device comprises a spanwise duct 10 which may be formed with a rearwardly directed coutinuous slot or may be provided with longitudinally spaced nozzles. The duct is supplied with compressed air or exhaust gases which it ejects into chordwise ducts 9 arranged to eject at 2 through the aperture formed between the trailing edge flaps 6 and the wing. The leading edge of the wing is provided with a nose flap 4 hinged about its lower edge so that when depressed it forms a gap 1 with the wing. The ejector effect of the nozzle 10 creates an airflow through the gap 1 and the duct 9 to control the airflow over the leading edge of the wing and the upper surface of the flap 6. In an alternative arrangement, Fig. 3 (not shown), the duct 10 may comprise two concentric ducts, one supplied with compressed air and the other with exhaust gases. In a further arrangement, Fig. 5 (not shown), the trailing edge of the wing may be provided with a first flap to which is pivoted a second flap. The nozzle 10 and the duct 9 may be installed inside the first flap to draw air from the gap formed between the flap and the wing and eject it through the gap formed between the first and second flaps. The nozzle 10 may be located on the hinge axis of the first flap and arranged to rotate therewith. The Specification as open to inspection under Sect. 91, comprises also a number of embodiments in which a is provided with a single trailing edge flap only and air inlet slots are provided in the fixed upper surface of the wing. A further embodiment is described applied to fuselages and nacelles in which continuous circumferential air inlet and outlet slots are formed in the outer panelling, ejector devices being mounted within the body between the slots. This subject-matter does not appear in the Specification as accepted.