| 摘要 |
The present invention relates to a blade (10) for a tilt rotor aircraft and, more specifically, to a blade ( 10) for a tilt rotor aircraft, capable of reducing energy required for taking off and landing or hovering flight by dispersing or offsetting vortex generated at a lower end of the blade (10) when a tilt rotor aircraft is taking off and landing or is hovering. The blade (10) includes: a rotor (100) installed on the outer side of the blade (10); a rear end flap (200) installed at a rear end of the blade (10) to vertically rotate; and a front end flap (300) installed at a front end of the blade (10) to vertically rotate and attached to a lower end of the blade (10). |
