| 发明名称 |
AIRFOIL FOR ROTOR BLADE WITH REDUCED PITCHING MOMENT |
| 摘要 |
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, a tip region extending from a radial extent of the main region to a blade tip, and a trailing edge. A portion of one of the root region, the main region and the tip region has an airfoil profile section including a trailing edge reflex camber relative to a base airfoil shape of a remainder of the one of the root region, the main region, and the tip region to reduce pitching moment of the rotor blade while maintaining a positive aerodynamic characteristic of the base airfoil shape. The reflex camber extends 20% of a blade chord from the trailing edge. |
| 申请公布号 |
US2016122011(A1) |
申请公布日期 |
2016.05.05 |
| 申请号 |
US201514954362 |
申请日期 |
2015.11.30 |
| 申请人 |
Sikorsky Aircraft Corporation |
发明人 |
Bagai Ashish |
| 分类号 |
B64C27/467;B64C27/46;B64C27/473 |
主分类号 |
B64C27/467 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. 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; a tip region extending from a radial extent of the main region to a blade tip; and a trailing edge extending from at least the main region toward the tip region, wherein a portion of one of the root region, the main region and the tip region has an airfoil profile section including a trailing edge reflex camber relative to a base airfoil shape of a remainder of the one of the root region, the main region, and the tip region to reduce pitching moment of the rotor blade while maintaining a positive aerodynamic characteristic of the base airfoil shape, the reflex camber extending 20% of a blade chord from the trailing edge. |
| 地址 |
Stratford CT US |
