Aerodynamic structures and their manufacture

Abstract

Abstract 1,128,331. Boundary layer control. HANDLEY PAGE Ltd., J. B. EDWARDS, and A. A. BLYTHE. 27 Jan., 1966 [27 Jan., 1965], No. 3638/65. Heading F2R. [Also in Division B7] A surface to which boundary layer suction is applied, for example an aircraft wing or fuselage skin 1 has an elongate slot 6, undercut surfaces 11 within the slot and an elongate element 12 (e.g. of aluminium or nylon) disposed within the slot. The element has an outer surface 14 shaped to complete the outer contour of the skin and its edges are spaced from the adjacent edges of the slot to form slits 2 to which suction is applied through apertures 9. One or both walls of each slit may be inclined, for example at 3-5 degrees to the normal to the surfaces 14 15 so that the slit tapers, as shown, and one edge of the slit may be raised relative to the other, for example by the width of the slot (e.g. 0.005 inch), to stabilize the boundary layer flow. The undercut surfaces 11 may be formed as shown in portions 17 upstanding from the base of the slot and be engaged by legs 18 of the element 12 extending between the portions 17. The element may be pliable to snap in place, or may be deformed by running a tool through the space 20. It may also be held by adhesive, bolts or rivets. The upstanding portions 17 may be integral with the skin, as shown, or formed by a separate channel section member secured in the face of the slot (Fig. 2, not shown). Alternatively (Fig. 3, not shown) a single upstanding portion is used with undercut surfaces on opposite sides, or the undercut surfaces may be in the side walls of the slot (Fig. 4, not shown). The element may be formed by short lengths placed side by side, which may then be dropped into a space at the end of a slot where the upstanding portion is omitted, and slid over the end of the upstanding portion (Fig. 5, not shown).

Inventors

• 👤 Edwards Joseph Brien
• 👤 Blythe Alan Avery

Bibliographic Details