A rotor blade for a rotary wing aircraft includes a root region extending from a rotor head to about 15% to 20% of a blade radius, a main region extending from a radial extent of the root region to about 80% to 95% of the blade radius, and a tip region extending from a radial extent of the main region to a blade tip. At least a portion of one of the root region, the main region and the tip region includes an airfoil profile section defined by a scaled set of coordinates in which a set of y/c coordinates listed in Table I are scaled by a selected factor.
Airfoil for rotor blade with reduced pitching moment
2016-03-15
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
ROTOR BLADE ASSEMBLY WITH HIGH PITCHING MOMENT AIRFOIL SECTION FOR A ROTARY WING AIRCRAFT
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