Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Patent
1999-02-09
2000-12-19
Swiatek, Robert P.
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
244201, B64C 314, B64C 338, B64C 2306
Patent
active
061618020
ABSTRACT:
An airplane has a plurality of airfoils with leading edges. A partition and a nose cap are located at a forward surface of the airfoil, creating upper and lower cavities. The nose cap may be positioned in an extended position or a retracted position. The nose cap is retracted when the airplane reaches supersonic speed. At supersonic speed, a shock wave forms on the leading edge of the airfoil. A compression zone forms 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 nose cap is extended to achieve optimal airfoil efficiency. Forward or rearward gaps may be opened between the nose cap and the main body portion of the airfoil to allow airflow from the lower cavity below the partition to the upper cavity above the partition to selectively increase or decrease lift on the airfoil.
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Bradley James E.
Lockheed Martin Corporation
Swiatek Robert P.
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