Airfoil for rotor blade with reduced pitching moment
AssigneeSikorsky Aircraft Corporation
InventorAshish Bagai
Life of this patent
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Abstract
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.
Claims10
A rotor blade for a rotary wing aircraft comprising:
- 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 including an airfoil profile section defined by a scaled set of coordinates in which a set of x/c coordinates defined as a ratio of an x coordinate to a blade chord length, and y/c coordinates defined as a ratio of a y coordinate to the blade chord length, listed in Table I are scaled by a selected factor.
A helicopter having a rotor system with a plurality of rotor blades, each rotor blade comprising:
- 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 including an airfoil profile section defined by a scaled set of coordinates in which a set of x/c coordinates defined as a ratio of an x coordinate to a blade chord length, and y/c coordinates defined as a ratio of a y coordinate to the blade chord length, listed in Table I are scaled by a selected factor.
Dependencies are inferred from the claim text.