A rotary-wing aircraft blade airfoil for use with a rotary-wing aircraft such as a helicopter. The airfoil satisfies the following four conditions: a first condition in which a blade thickness has its maximum value at a position within a range from 30% chord to 40% chord; a second condition in which a camber has its maximum value at a position within a range from 15% chord to 25% chord, and that a slope of the camber changes from decreasing into increasing at a position within a range from 45% chord to 55% chord; a third condition in which the upper blade height has its maximum value at a position within a range from 25% chord to 35% chord; and a fourth condition in which the lower blade height has its maximum value at a position within a range from 35% chord to 45% chord.
ROTARY-WING AIRCRAFT BLADE AIRFOIL, BLADE HAVING THE BLADE AIRFOIL, AND ROTARY-WING AIRCRAFT INCLUDING THE BLADE
2021-08-05
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2022
|European Patent Office | 2019
|European Patent Office | 2019
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