Advanced airfoils for helicopter rotor application

Details Advanced airfoils for helicopter rotor application Advanced airfoils for helicopter rotor application

1979-09-28

1982-02-09

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

416237, B64C 2746

Patent

active

043147950

ABSTRACT:
A family of airfoils for use in rotary wing aircraft, particularly helicopters, is disclosed. The family is characterized by having a maximum c.sub.1.sbsb.max at M=0.4 and maximum delay in drag divergence while maintaining zero lift pitching moment levels c.sub.m.sbsb.o correctable within the range of -0.01 to +0.01. The present family of airfoils provide high lift at maximum angle of attack when the blade is retreating and maximum delay in drag rise or drag divergence when the blade is advancing. The airfoil section of the family enable a helicopter rotor to counteract, more efficiently, the rolling moment which would otherwise be induced by a rotorcraft's forward flight; this is achieved by the present family of airfoils while maintaining the airfoil sectional pitching moment coefficient at or about zero thereby enabling the blade in which the airfoil sections are incorporated to impose minimum structural loads on the rotorcraft's control system.

REFERENCES:
patent: 2614639 (1952-10-01), Richard
patent: 3173490 (1965-03-01), Stuart
patent: 3343512 (1967-09-01), Rasmussen
patent: 3721507 (1973-03-01), Monteleone
patent: 3728045 (1973-04-01), Balch
patent: 3822105 (1974-07-01), Jepson
patent: 4142837 (1979-03-01), deSimone

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