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US 5,209,643 AGranted
Tapered propeller blade design
AssigneeCessna Aircraft Company
InventorGregory M. Cole
Life of this patent
Estimating the term…
Abstract
An aircraft propeller blade utilized in subsonic flight at relatively slow turning applications with relatively high power coefficients. The blade in plan form is tapered at both ends with the maximum chord approximate the 44% percent station of the blade, the leading edge of the blade being swept behind the longitudinal axis of the blade near its tip and the trailing edge is convex and essentially straight from its maximum chord outward to the tip.
Claims6
An aerial propeller blade utilized in subsonic flight regions comprising:
- a blade having leading and trailing edges, a tip, a cylinder shank having a rotational longitudinal axis, and a transition area between the shank and the blade, in plan form the blade is tapered from both ends with a maximum chord substantially in a range between the 44% and 50% blade radius stations, the leading edge of the blade being swept behind the rotational longitudinal axis of the blade and the trailing edge is convex and substantially straight from its maximum chord outward to the tip and inclined toward the longitudinal axis.
An aerial propeller blade utilized in subsonic flight regions comprising:
- a blade having leading and trailing edges, a tip, a cylindrical shank, and a transition area between the shank and the blade, in plan form the blade is tapered from both ends with its maximum chord substantially at its 44% blade radius station, the leading edge of the blade being swept behind the longitudinal axis of the blade and the trailing edge is convex and essentially straight from its maximum chord outward to the tip and inclined toward the longitudinal axis.
Dependencies are inferred from the claim text.