High performance low noise helicopter blade aerodynamic design

摘要

A main rotor helicopter blade is presented for generating higher lift with less drag and delaying stall at high Mach numbers using aft camber. The difference between a chord line (1250) of the cross-section and a camber line (1260) of the cross-section increases from a leading edge (1210) of the cross-section to a maximum (1290) between the leading edge and a midpoint (1270) of the chord line and decreases to a trailing edge (1220) of the cross-section, wherein a slope of the difference sequentially decreases from the leading edge to the maximum, increases negatively from the maximum, decreases negatively, and increases negatively to the trailing edge, the latter optionally via a further negative decrease, to produce the aft camber of the blade.