| 摘要 |
718,421. Boundary layer control. FAIREY AVIATION CO., Ltd., and HOOPER, M. S. Feb. 4, 1952 [Feb. 12 1951], No. 3383/51. Class 4 Boundary layer control means for fluid flowing relatively to a boundary wall is provided by the wall consisting of an inner and an outer perforated skin, 18 and 17, with a porous or granular filler 19 and means for drawing the fluid through all three layers. The stressed skin 11 of the aerofoil shown in Fig. 1 is formed with ridges 15 and 16 to correspond to ridges 20 in the boundary wall, and which may be fastened thereto by rivets, or by screwing down into spars 12. The spaces between skins 18 and 11, and consecutive ridges, form ducts through which the indrawn fluid may be guided. The ducts are joined to a manifold at the root of the wing, to which the suction means is also coupled. Control valves may be provided to restrict the flow through all or certain of the ducts. Deicing may be accomplished by passing an electric current through the filler 19 by electrodes 52 and 53 or electrode 51 and the perforated skins, which filler may be a conductor, e.g. carbon granules, or coated with a suitable conducting material. Provision may be made for similar boundary layer control of any part of the aircraft surface. The degree of perforation of the inner and outer skins, and the porosity of the filler may be varied from place to place. The filler may be confined by metal gauze or the like, to leave an air gap between it and the inner or outer skin.
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