| 摘要 |
PROBLEM TO BE SOLVED: To provide a rotor blade of rotary wing aircraft equipped with an enhanced performance in a high-speed flight, capable of reducing high-speed impact sounds, and having a good maneuvering performance. SOLUTION: The wing root of each rotor blade 101 is attached to a rotor head for rotary drive while the central part extends straight from the wing root, and the wing end part extends outward from the central part so that a specified wing shape is established having a form bounded by a leading edge 23, side edge, and trailing edge 30. At the leading edge 23 of the wing end part, the sweep-back angleλ(r) in a position at the distance (r) from the rotation center of the rotor means the formula given below, where R is the rotor blade length of the rotary wing aircraft, M∞is the max. flight Mach number as the limit flying speed of a rotary wing aircraft, MTIP is the wing tip Mach number as the wing tip velocity in hovering, and Mdd is the resistance disperse Mach number decided by the wing form of the wing tip part.
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