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607,457. Boundary layer control. GOODYEAR AIRCRAFT CORPORATION. Feb. 5, 1946, No. 3590. Convention date, Feb. 10, 1945. [Class 4] [Also in Group XXVI] An aircraft is provided with a jet engine with a nozzle terminating at the rear of the fuselage, a casing spaced from and surrounding the jet tube for substantially its full length forming a suction pump operated by the exhaust gases being connected to slots in the wings for promoting boundary layer suction. The aircraft illustrated is provided with an internal-combustion engine 12 driving a propeller in addition to the gas turbine 13, the exhaust of which discharges through the jet tube 14. The turbine and tube are enclosed in a casing 25 provided with a forward extension 26 into which is led the exhaust pipe 16 of the engine 12. Boundary layer air is drawn through slots 20 in the surfaces of the wings, ailerons and flaps into conduits 21 connected with the casing 25, the necessary suction being provided by the exhaust from the turbine and/or the engine 12, under the control of valves 28, 29. The turbine and jet tube are cooled by the air flowing between the casings 14 and 25. The starter motor 27 may be used in the event of failure of the turbine to promote sufficient suction to remove the boundary layer. The ailerons or flaps 8, Fig. 4, are hinged to the lower surfaces of the wings 7, the gaps in the upper surfaces being bridged by strips 11 which preserve the aerofoil profile. Ducts 22 communicate with the slots 20 in the ailerons or flaps, and by flexible connections 23 with the main conduits 21. Valves 17 may be provided to control the suction at the lower wing slots.
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