In a rotary-wing aircraft blade airfoil included in a rotary-wing aircraft such as a helicopter, it is assumed that: a position of a rear end of a chord of the airfoil with respect to a front end of the chord is 100% chord; a position of a blade upper surface, the position being measured from the chord, is an upper blade height; and a position of a blade lower surface, the position being measured from the chord, is a lower blade height. The rotary-wing aircraft blade airfoil satisfies the following four conditions: a first airfoil condition, which is a condition that a blade thickness has its maximum value at a position within a range from 30% chord to 40% chord; a second airfoil condition, which is a condition that 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 airfoil condition, which is a condition that the upper blade height has its maximum value at a position within a range from 25% chord to 35% chord; and a fourth airfoil condition, which is a condition that 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
SCHAUFELBLATT EINES DREHFLÜGELFLUGZEUGES, SCHAUFEL MIT DIESEM SCHAUFELBLATT UND DREHFLÜGELFLUGZEUG MIT DIESEM SCHAUFELBLATT
PROFIL DE PALE D'AÉRONEF À VOILURE TOURNANTE, PALE COMPORTANT CE PROFIL ET AÉRONEF À VOILURE TOURNANTE COMPORTANT CETTE PALE
2022-03-16
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2021
|European Patent Office | 2019
|European Patent Office | 2019
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