Patent ID: 7854593

Claim:
A main rotor blade section comprising: an inboard region; and a main region outboard of said inboard region, said main region including an airfoil profile section which defines an airfoil thickness along a chord line within said airfoil profile section, said airfoil profile section having leading edge and a trailing edge, an upper airfoil surface and a lower airfoil surface which extend between said leading edge and said trailing edges as defined by a set of coordinates in which an airfoil thickness is plotted against a non-dimensional distance from said leading edge of said airfoil profile section along said chord line, as a set of Y/C coordinates scaled by a desired factor at a given X/C as listed in Table I, wherein X is the linear displacement along the chord line extending between the leading edge and the trailing edge, C is the chordal length of the airfoil cross section measured between the airfoil leading edge and the airfoil trailing edge; and Y is a transverse displacement of the airfoil surface from the chord line.