Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Patent
1976-12-13
1978-07-11
Barefoot, Galen L.
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
244214, 244134B, B64C 2104
Patent
active
040996913
ABSTRACT:
An improved boundary layer control system is particularly useful in applications where controlled air is to be injected into a boundary layer region adjacent to a surface of an aircraft wing. The controlled air is obtained from an air source having a temperature and a pressure which are substantially greater than ambient temperature and pressure, such as that obtained from a jet engine bleed air source. A number of manifolds are located in spanwise arrangement along the wing and serve to conduct the air from the source to a plurality of nozzle penums, each of which includes a plurality of spanwise-spaced apertures for injecting air into a portion of the boundary layer region. The manifolds are interconnected by compressible bellows and are mounted so that respective inboard ends are fixed and respective outboard ends are free to move longitudinally. At least one nozzle plenum is interconnected with and supported by each manifold through use of a pair of flexible, outboard feeder ducts and an intermediate, non-flexible feeder duct. The plurality of apertures are located in a front wall member of each nozzle plenum which is located in a spanwise slot in the leading edge of the wing and maintained substantially flush with the leading edge of the wing by upper and lower, spanwise tongues which are received in corresponding upper and lower spanwise grooves in the portions of the wing adjacent to the slot. Apparatus is also disclosed to limit the relative transverse movement of each nozzle plenum with respect to its associated manifold, to bleed controlled air from the plurality of manifolds when a substantial number of the apertures of the nozzle plenums are obstructed due to ice or the like, and to seal a separation between adjacent nozzle plenums to prevent substantial airflow between the exterior airstream and the wing interior.
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Ernst et al., "YC-14 System for Leading Edge Boundrary Layer Control," AAAA paper, No. 74-1278, 10-30-74.
Swanson Everts W.
Wehrman Marvin D.
Barefoot Galen L.
The Boeing Company
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