Helicopter rotor blades

Details Helicopter rotor blades Helicopter rotor blades

1991-10-10

1992-12-29

Kwon, John T.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

416DIG5, B64C 1118

Patent

active

051747219

ABSTRACT:
Flow separation behind the notch region of a swept tip of a helicopter rotor blade is reduced by features of the geometry and aerodynamic characteristics of the notch region itself. In particular it has been found beneficial for a forwardly swept leading edge portion to extend at an angle between 30 degrees and 55 degrees from a reference line parallel to a blade pitch change axis and the leading edge of the aerofoil in the notch region incorporates blade droop.

REFERENCES:
patent: 3053325 (1962-09-01), Ferreira
patent: 3721507 (1973-03-01), Monteleone
patent: 3972646 (1976-08-01), Brown et al.
patent: 4012172 (1977-03-01), Schwaar et al.
patent: 4063852 (1977-12-01), O'Connor
patent: 4142837 (1979-03-01), de Simone
patent: 4880355 (1989-11-01), Vuillet et al.
patent: 5035577 (1991-07-01), Damongeot
patent: 5064345 (1991-11-01), Kimball

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