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. The difference between a chord line (1650) of the cross-section and a camber line (1660) of the cross-section sequentially increases from a leading edge (1610) of the cross-section to a first maximum (1690) between the leading edge and a midpoint (1670) of the chord line, decreases to a first minimum (1695) between a trailing edge (1620) of the cross-section and the midpoint, increases to a second maximum (1698) between the trailing edge and the midpoint, and decreases to the trailing edge, wherein a slope of the difference sequentially decreases from the leading edge to the first maximum, increases negatively from the first maximum, decreases negatively to the first minimum, increases from the first minimum, decreases to the second maximum, and increases negatively from the second maximum to the trailing edge, to produce an aft camber of the blade.