Abstract: According to one embodiment, a quality analyzer receives aerodynamic performance data for a part that has been manufactured according to a design. The aerodynamic performance data expresses aerodynamic performance of the part as calculated from a plurality of coordinates measured on the part. The quality analyzer determines whether the aerodynamic performance data for the part satisfies minimum aerodynamic performance requirements.

Abstract: According to one embodiment, a quality analyzer receives aerodynamic performance data for a part that has been manufactured according to a design. The aerodynamic performance data expresses aerodynamic performance of the part as calculated from a plurality of coordinates measured on the part. The quality analyzer determines whether the aerodynamic performance data for the part satisfies minimum aerodynamic performance requirements.

Abstract: One embodiment of the present invention is a main rotor helicopter blade for generating higher lift with less drag and delaying stall at high Mach numbers. A cross-section of this blade includes aft camber. The 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 a trailing edge of the cross-section and a midpoint of the chord line and decreases to the trailing edge producing the aft camber of the blade. The aft camber generates higher lift with less drag and delays stall at high Mach numbers.

Abstract: A flow control device is disclosed including a flow control surface over which fluid is designed to flow in a predetermined direction. Vortex generators are associated with the flow control surface. Each respective vortex generator has a pivot axis that forms an acute angle with respect to the predetermined direction and is capable of being positioned in both of an extended state, in which the respective vortex generators function to create a swirling fluid flow, and a retracted state, in which the respective vortex generators are pivoted via the pivot axis so as to lie adjacent to the flow control surface. An actuator is associated with each of the vortex generators, each actuator adapted to position the associated vortex generator between the extended and retracted states. The flow control device is disclosed to be used in tiltrotor vehicles.

Abstract: One embodiment of the present invention is a main rotor helicopter blade for generating higher lift with less drag and delaying stall at high Mach numbers. A cross-section of this blade includes aft camber. The 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 a trailing edge of the cross-section and a midpoint of the chord line and decreases to the trailing edge producing the aft camber of the blade. The aft camber generates higher lift with less drag and delays stall at high Mach numbers.