Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Patent
1997-01-10
1998-11-17
Grant, William
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
244 35R, 244 35A, 244123, 244130, 416235, 416243, B64C 316, B64C 336, B64C 1118
Patent
active
058365494
ABSTRACT:
A jet airplane capable of supersonic flight has airfoils with leading edges. Each leading edge has a cavity which extends for substantially the entire length of the airfoil. The leading edge also has a cover which is approximately the same size as the cavity. The cover has an open position and a closed position. When the cover is in the open position, the leading portion has a concave profile. When the cover is in the closed position, the leading portion has a convex profile that gives the airfoil a conventional shape. The cover is rotated to the open position when the airplane reaches supersonic speed. At supersonic speed, a shock wave forms on the leading edge of the airfoil. However, the cavity forms a compression zone between the shock wave and the leading edge, diverting the heat and pressure of the shock wave away from the airfoil. Downstream from the compressed zone, pressure wakes form along the airfoil and cool the airfoil. At subsonic speed, the cover is rotated to the closed position to achieve optimal airfoil efficiency.
REFERENCES:
patent: 2136403 (1938-11-01), Vance et al.
patent: 2916230 (1959-12-01), Nial
patent: 3568956 (1971-03-01), Swanson
patent: 4405102 (1983-09-01), Taylor
patent: 5299762 (1994-04-01), Kosson et al.
Bradley James E.
Grant William
Lockheed Martin Corporation
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