Patent ID: 8016566
Filing Date: 2011-09-13
Classification: B64C,Y10S,Y10T

Abstract:
1. A main rotor helicopter blade for generating higher lift with less drag and delaying stall at high Mach numbers comprising: a cross-section, wherein a difference between a chord line of the cross-section and a camber line of the cross-section increases from a leading edge of the cross-section to a maximum between the leading edge and a midpoint of the chord line and decreases to a trailing edge 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, and wherein the slope increases negatively from the maximum, decreases negatively, and increases negatively to the trailing edge to produce an aft camber of the blade that generates higher lift with less drag and delays stall at high Mach numbers.