High performance blade for helicopter rotor

Details High performance blade for helicopter rotor High performance blade for helicopter rotor

1981-03-13

1983-07-12

Hornsby, Harvey C.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

416DIG2, B64C 2746

Patent

active

043927815

ABSTRACT:
The present invention relates to a high performance blade for helicopter rotor presenting an aerodynamic surface produced by profiles of which the aerodynamic twist increases from the end profile towards the root profile and is then reversed and becomes zero at the fastenings of the blade. According to the invention, the angle of twist formed by the zero lift chord C.sub.o of a profile of the aerodynamic surface and a reference plane P passing through the center of the fastenings of the blade to the hub of the rotor, is, for the end profile, at the most equal to a value .theta..sub.1 of 0.3 degrees. The invention is more particularly applied to the obtaining of rotary wings, for example for helicopters, capable of very high performances, particularly in rapid forward flight under high load.

REFERENCES:
patent: 3902821 (1975-09-01), Robinson
patent: 4248572 (1981-02-01), Fradenburgh
patent: 4325675 (1982-04-01), Gallot et al.

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