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.
HIGH PERFORMANCE LOW NOISE HELICOPTER BLADE AERODYNAMIC DESIGN
CONCEPTION AERODYNAMIQUE DE PALES D'HELICOPTERE HAUTE PERFORMANCE PEU BRUYANTES
2015-09-29
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Low-noise rotor blade aerodynamic configuration of helicopter
European Patent Office | 2021
|Aerodynamic Study of Helicopter Blade Sections
NTIS | 1968
|Aerodynamic Impacts of Helicopter Blade Erosion Coatings
AIAA | 2012
|Aerodynamic Impacts of Helicopter Blade Erosion Coatings
British Library Conference Proceedings | 2012
|Aerodynamic design optimization of a helicopter rotor blade-sleeve fairing
Springer Verlag | 2018
|