Combination boundary layer control system for high altitude airc

Details Combination boundary layer control system for high altitude airc Combination boundary layer control system for high altitude airc

1987-08-12

1989-02-28

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft structure

244209, 60267, B64C 138, B64C 2106

Patent

active

048078310

ABSTRACT:
The invention comprises a combination boundary layer control system that utilizes both suction and cryogenic wall cooling to reduce aircraft drag. The invention is particulary useful in circumstances where liquid hydrogen or other cryogenic fuels are used to operate the aircraft.
In the preferred embodiment of the invention, a network of D-tube ducts are provided that are fluidly connected to a cryogenic fluid source. These cryogenic fluid ducts are selectively fed cryogenic fluid to reduce aircraft surrface temperature and promote adhesion of boundary layer air to the aircraft. An air duct system is also provided to apply suction to the aircraft surface in order to remove the boundary layer at low altitude. The suction is applied by means of a multitude of minute holes in the aircraft skin which are fluidly connected to the air duct system.

REFERENCES:
patent: 2867391 (1959-01-01), Jacobsen
patent: 2958482 (1960-11-01), Summers, Jr.
patent: 3093350 (1963-06-01), Wilkins
patent: 3126718 (1964-03-01), Flamand
patent: 3129754 (1964-04-01), Menzel
patent: 3253423 (1966-05-01), Sonnabend
patent: 3556443 (1971-01-01), Kidwell
patent: 4273304 (1981-06-01), Frosch et al.
patent: 4505124 (1985-03-01), Mayer

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