Lifting shock wave cancellation module

Details Lifting shock wave cancellation module Lifting shock wave cancellation module

1983-12-27

1986-04-15

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft structure

Fuselage and body construction

244130, 244 35A, 244198, B64C 100

Patent

active

045822760

ABSTRACT:
An aerodynamic structure which when included into the design of a supersonic aircraft provides the aircraft with a higher lift/drag ratio than has been obtainable previously in supersonic aircraft design. In a preferred embodiment, the aerodynamic structure has the general shape of a modified U-channel with each of the legs of the U-channel being configured in cross section as an isosceles triangle and extending from a cross plate. The vertical apices of each triangle face each other and are separated so that shock waves originating from the leading edges of the aerodynamic structures are cancelled by expansion waves being generated from the vertical apices. At supersonic speeds lift of the aircraft is created by a pressure field generated by a shock-expansion system acting on the cross plate of the U-channel.

REFERENCES:
patent: 3137460 (1964-06-01), Owl, Jr. et al.
patent: 3942746 (1976-03-01), Carter et al.
patent: 4243188 (1981-01-01), DeBlois
Liepmann et al., Elements of Gasdynamics, "Waves in Supersonic Flow, .sctn.4.19 Drug Reduction", May 1967, pp. 115-118.

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