Blade with swept-back tip for the rotary wings of an aircraft

Details Blade with swept-back tip for the rotary wings of an aircraft Blade with swept-back tip for the rotary wings of an aircraft

1997-11-18

1999-12-14

Lopez, F. Daniel

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

416228, 416238, 416DIG5, B46C 1118

Patent

active

06000911&

ABSTRACT:
The present invention relates to a blade with a swept-back tip for a rotary wings of an aircraft, a blade being formed of successive elemental cross sections. The blade is divided into different regions, with the chord length L and the offset y'f of the center of pressure from the pitch-change axis and the relative thickness of each elemental section are optimized for high-speed flight. The first region has a linearly increasing chord length, the second region has the maximum and constant chord length, the third region has a linearly decreasing chord length and the fourth region has a decreasing chord length according to a parabolic function. The offset of the aerodynamic center is positive and increases in proportional to the distance in the first region, is at its maximum and constant in the second region, and decreases linearly and become negative in the third region.

REFERENCES:
patent: 3066742 (1962-12-01), Castles, Jr.
patent: 4130377 (1978-12-01), Blackwell, Jr.
patent: 4880355 (1989-11-01), Vuillet et al.
patent: 5035577 (1991-07-01), Damongeot
patent: 5332362 (1994-07-01), Toulmay et al.
French Search Report dated Jun. 23, 1997, 3 pages.

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