Passive vortex lift control

Details Passive vortex lift control Passive vortex lift control

1984-05-14

1987-11-10

Blix, Trygve M.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

244207, B64C 2306

Patent

active

047052406

ABSTRACT:
A method of applying and controlling vortex lift to a unique high-lift airfoil (29) is described wherein the planform of the airfoil (29) comprises a swept-forward outer panel (31) and a swept-aft or unswept inboard panel (33). A leading edge vortex (37) is formed on (31) and attached flow is maintained on (33). The attached flow on (33) causes the vortex (37) of the airfoil (29) to turn downstream and also induces axial flow along axis of vortex (37). Both of these results serve to delay vortex burst. A high-lift trailing edge device (45) such as a mechanical flap as the circulation control concept will induce a high leading edge flow angularity and cause the vortex (37) to grow in strength, thereby increasing vortex lift. The vortex (37) replaces the high-weight, high-lift leading device that would otherwise be required.

REFERENCES:
patent: 2417189 (1947-03-01), Cornelius
patent: 2628043 (1953-02-01), Montgomery
patent: 2769602 (1956-11-01), Furlong
patent: 3480234 (1969-11-01), Cornish, III
patent: 4387869 (1983-06-01), Englar et al.
Flight International, "Forward-Swept-Wing Technology", by Graham Warwick, 22 May 1982, pp. 1317-1319.

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