Transition shoulder system and method for diverting boundary lay

Details Transition shoulder system and method for diverting boundary lay Transition shoulder system and method for diverting boundary lay

1996-05-28

1998-05-12

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft power plants

137 151, B64D 3302

Patent

active

057495424

ABSTRACT:
A diverterless engine inlet system that integrates a transition shoulder into a system for diverting air from the inlet of an aircraft engine. ????? The bump includes an isentropic compression surface raised outwardly from the body of the aircraft to form a portion of the inner surface of the inlet. The transition surface works with the compression surface to divert low energy boundary layer air from the inlet during aircraft operation.

REFERENCES:
patent: 3066892 (1962-12-01), Smith et al.
patent: 3137460 (1964-06-01), Owl, Jr. et al.
patent: 3667704 (1972-06-01), Assmann
patent: 4502651 (1985-03-01), Jungclaus et al.
patent: 4655413 (1987-04-01), Genssler et al.

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