Aeronautics and astronautics – Aircraft control – Rudders and empennage
Patent
1980-05-05
1981-09-29
Barefoot, Galen L.
Aeronautics and astronautics
Aircraft control
Rudders and empennage
244199, 244200, B64C 502, B64C 2100
Patent
active
042918537
ABSTRACT:
Disclosed is an airplane all-moving airfoil having a moment reducing apex for facilitating control of the airfoil. In a preferred embodiment, the apex protrudes forward from the leading edge of an all-moving horizontal stabilizer and operates through its aerodynamic effect on the stabilizer to reduce the moment required to maintain and vary the stabilizer position. Counter-rotating airflow vortices produced by the apex reduce the rearward displacement of the center of pressure on the stabilizer as the stabilizer is deflected into an increasing angle of attack. As a result, lighter weight hydraulic stabilizer and elevator actuating mechanisms can be employed. In a preferred embodiment an aeroelastically flexible apex is employed to enhance moment reduction at high angles of attack.
REFERENCES:
patent: 2650752 (1953-09-01), Hoadley
patent: 2769602 (1956-11-01), Furlong
patent: 2800291 (1957-07-01), Stephens
patent: 2950879 (1960-08-01), Smith
patent: 3008291 (1961-11-01), Hardgrave
patent: 3370810 (1968-02-01), Shevell et al.
patent: 3415468 (1968-12-01), Labombardo
patent: 3417946 (1968-12-01), Hartley
Soderman, "Aerodynamic Effects of Leading-Edge Serrations on a Two-Dimensional Airfoil," NASA TMX-2643, Sep., 1972.
Barefoot Galen L.
The Boeing Company
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