Helicopter rotor blade

Details Helicopter rotor blade Helicopter rotor blade

1984-06-19

1987-05-26

Garrett, Robert E.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

416228, B64C 2746

Patent

active

046681698

ABSTRACT:
An outboard region of a helicopter rotor blade of aerofoil cross section has a thickness to chord ratio not greater than twelve percent and an inboard region has a thickness to chord ratio greater than twelve percent. Preferably, the thickness to chord ratio of the inboard region is greater than eighteen percent and may increase towards the root end to about twenty four percent. The inboard region may extend outwardly to a position not exceeding sixty percent of an operating radius of the rotor blade.

REFERENCES:
patent: 3782856 (1974-01-01), Salkind et al.
patent: 4248572 (1981-02-01), Fradenburgh
U.S. Ser. No. 318,662 filed 6-1943, Bitterli et al.

Affiliated with

Also associated with

Rating

Helicopter rotor blade does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Helicopter rotor blade, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Helicopter rotor blade will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-700710