Rotor blade for a rotary-wing aircraft

Details Rotor blade for a rotary-wing aircraft Rotor blade for a rotary-wing aircraft

1995-08-01

1997-03-11

Larson, James

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

416242, B64C 27467

Patent

active

056094728

ABSTRACT:
A rotor blade for a rotary-wing aircraft, of an airfoil section has a basic blade thickness at 12% chord length, a portion of an increased blade thickness between the leading edge and a point corresponding to about 90% chord length, a maximum blade thickness at a position shifted backward, a curvature distribution concentrated on the middle portion thereof, and a portion contiguous with the trailing edge and cambered. The drag coefficient of the airfoil section is small when the Mach number is about 0.6 and the lift coefficient is about 0.6, and the airfoil section has a large maximum lift coefficient and a large zero-lift drag divergence Mach number, and generates a small pitching moment.

REFERENCES:
patent: 4412664 (1983-11-01), Noonan
patent: 4459083 (1984-07-01), Bingham
patent: 4776531 (1988-10-01), Noonan
patent: 5344102 (1994-09-01), Nakadate et al.

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