Patent ID: 7252479

Claim:
A main rotor blade assembly for a rotary wing aircraft comprising: a main rotor blade root region containing a root attachment chord taken within said main rotor blade root region transverse to a feathering axis; a main rotor blade inboard region outboard of said main rotor blade root region, said main rotor blade inboard region containing an inboard chord within said main rotor blade inboard region transverse to said feathering axis; a main rotor blade main region outboard of said main rotor blade inboard region, said main rotor blade main region containing a main rotor blade maximum chord within said main rotor bade main region transverse to said feathering axis; a main rotor blade tip region outboard of said main region, said tip region containing a tip region chord within said main rotor blade tip region transverse to said feathering axis; and a blade chord defined between a leading edge and a trailing edge, said trailing edge defined along a root trailing edge of said main rotor blade root region, an inboard region trailing edge of said inboard main rotor blade inboard region, a main region trailing edge of said main rotor blade main region and a tip region trailing edge of said main rotor blade tip region, said inboard region trailing edge defining a point A and a point B, said point B outboard of said point A, said main region trailing edge defining a point C and a point D, said point D outboard of said point C, said blade chord increasing between said point A and said point B and decreasing between said point C and said point D, said main rotor blade maximum chord located between said point B and said point C.