FIELD: aviation.
SUBSTANCE: invention relates to aircraft engineering, particularly, to design and aerodynamic characteristics of rotorcraft aircraft propeller blades. Vane improvement method includes determination of initial radius of leading edge of every aerodynamic profile (15, 25), increasing radius of initial circle (15.25) of leading edge of every aerodynamic profile (10) of said blade. Then its front edge (5) is moved from half-profile (21) of trowel to side of semi-profile (11) of back, thus changing aerodynamic profile (10) of each cross section of said blade and curvature of each aerodynamic profile (10).
EFFECT: increasing in absolute value negative critical angle of attack of said blade, which increases aerodynamic characteristics of said blade at negative angle of attack compared to unmodified blade, wherein without significant deterioration of its aerodynamic characteristics at positive angle of attack.
13 cl, 12 dwg
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