GB474241A - Improvements in aeroplanes - Google Patents

Abstract

474,241. Propelling and controlling aircraft. JONG, A. DE, and VOLPERT, L. April 27, 1936, No. 11976. [Class 4] In an aeroplane having a thick wing of deep section and rounded leading edge mounted on the fuselage so that leading edge and upper surface are continuous across the span whilst the under surface is interrupted by the fuselage, a forwardly directed air inlet opening is formed in the fuselage nose and has a cross-sectional area approaching the maximum cross-sectional area of the fuselage, the opening being connected to the suction side of an air pump, the discharge side of which is in communication with one or more transversely extending slots formed in and confined to that part of the wing leading edge which is above the fuselage and, optionally, also extends for a short distance on each side thereof, the arrangement being such that all or substantially all of the air discharged by the pump is discharged through the slot or slots substantially upwardly and tangentially to the leading edge of the wing. In one form, Fig. 2, a fan c draws air through an opening d in the nose of fuselage band discharges it at e tangentially to the surface of the leading edge of wing a. Discharge openings p in the fuselage walls may be connected to the discharge side of the fan during starting. In a modification, Fig. 2, multiple discharge openings e are defined by elements f rotatable about transverse axes g which are automatically adjustable in accordance with pressures of the relative wind and of the outflowing air. In a further modification, Fig. 3, a centrifugal fan c is fitted in the wing nose, and discharges air through opening e. The wing may be provided with slots h as shown in Figs. 4 and 5. These are stated to increase the propulsion due to the suction effect and run longitudinally from the section of greatest wing depth to the trailing edge, are directed obliquely toward the fuselage, and increase in section from extrados to intrados. A fuselage may be employed of which the cross-section is reduced rearwardly to a minimum at the trailing edge of the wing at which point the fuselage is only of such cross-section as is necessary for the support of an empennage. Valve-controlled discharge openings such as r, Fig. 4, may be provided for lateral control. The aerofoil section in the region of the discharge opening e may have a steeper nose than the remainder of the wing as shown in Fig. 7, the leading edge n in this part being inset with relation to the leading edge m of the remainder.