Aircraft boundary layer control system with discharge transpirat

Details Aircraft boundary layer control system with discharge transpirat Aircraft boundary layer control system with discharge transpirat

1995-11-30

1998-06-30

Kashnikow, Andres

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

244207, 244208, 244130, B64C 2106

Patent

active

057721564

ABSTRACT:
An improvement to boundary layer control system, including a transpiration panel (58) for transpiring suction air in a distributed manner, is provided. The transpiration panel (58) replaces the discharge nozzle of prior art flow control systems. The transpiration panel (58) is generally a rigid panel having a plurality of small holes (62) extending from an inner panel surface (56) to a smooth outer panel surface (54). The transpiration panel (58) is positioned flush with an external aircraft surface in a region where laminar flow control is not being attempted. Exemplary subsonic and supersonic boundary layer control systems including the transpiration panel (58) are provided. A preferred location of the transpiration panel (58) for the subsonic application is the underside of a wing (80), near the leading edge. A preferred location of the transpiration panel (58) for the supersonic application including on the upper surface of a wing (114) near the fuselage (118), in a turbulent wedge region.

REFERENCES:
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patent: 2873931 (1959-02-01), Fleischmann
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patent: 3692259 (1972-09-01), Yuan
patent: 3933327 (1976-01-01), Cook et al.
patent: 4008866 (1977-02-01), Rethorst
patent: 4664345 (1987-05-01), Lurz

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