초록 ▼

A family of airfoils for use in a high solidity factor blade having a leading edge portion and a trailing edge portion, a tip portion, and a root portion, has a plurality of airfoil sections. Each section has: one of any of a plurality of camber lines extending from the leading edge portion to the t

A family of airfoils for use in a high solidity factor blade having a leading edge portion and a trailing edge portion, a tip portion, and a root portion, has a plurality of airfoil sections. Each section has: one of any of a plurality of camber lines extending from the leading edge portion to the trailing edge portion, the camber lines being scalable relative to each other, each having the same relative shape, the camber lines having a minimal slope from the leading edge to about a 40% chord and an apogee at about a 74% chord; a scalable thickness ratio of between about 2% to about 7.5%; and, a maximum thickness position which is located from about a 37.5% chord for an airfoil at the tip portion of the blade to about a 35.0% chord for an airfoil at the root portion of the blade.

대표청구항 ▼

An aircraft propeller blade having a root portion, and a tip portion, said blade comprising: a plurality of airfoil sections having a thickness ratio of between 7.5% and 2%; each section having along substantially the entire length thereof, a cross sectional shape characterized by; a parabolic leadi

An aircraft propeller blade having a root portion, and a tip portion, said blade comprising: a plurality of airfoil sections having a thickness ratio of between 7.5% and 2%; each section having along substantially the entire length thereof, a cross sectional shape characterized by; a parabolic leading edge, a camber having a minimal slope extending from the leading edge to about a 40% chord and having an apogee at a 74% chord, a gradual pressure recovery upper surface from about the 40% chord to a trailing edge, a concave lower surface from about the 40% chord to the trailing edge to generate life, said upper and lower surfaces merging into a relatively blunt trailing edge, and a maximum thickness positioned along the length of each airfoil section from said tip portion to said root portion, said maximum thickness of each airfoil section located from a 37.5% chord for an airfoil at said tip portion to a 35.0% chord at said root portion for an airfoil whereby said propeller blade forms one of an airfoil family.