Aeronautics and astronautics – Aircraft sustentation – Sustaining airfoils
Patent
1987-05-27
1988-10-11
Barefoot, Galen
Aeronautics and astronautics
Aircraft sustentation
Sustaining airfoils
244199, 244 45R, B64C 300, B64C 500
Patent
active
047765429
ABSTRACT:
A system for deterring subsonic airplane stall-spin entry wherein a highly swept wing tip mounted lifting surface panel 18 (FIGS. 1-3) is attached to the tip of a main wing panel 14 and provides a stabilizing vortex lift to the aircraft at an angle of attack slightly greater than the normal angle of attack used in climbing flight. This vortex lift enhances roll damping at high angles of attack and serves to prevent airplane stall-spin entry. FIG. 4 shows an alternate form of the invention wherein the wing tip mounted lifting surface panel 48 is provided with a forward highly swept leading edge. For sharp leading edges a leading edge sweep for the wing tip mounted lifting surfaces is approximately forty-five degrees while, for blunt leading edge surfaces, a greater degree of sweep is employed to generate the vortex lift.
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Gulfstreamer, vol. 5, No. 6, Winter 1976.
Barefoot Galen
Fiorito Lynn M.
Nelson Wallace J.
Vigyan Research Associates, Inc.
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