FIELD: aviation.
SUBSTANCE: present invention relates to aircraft engineering, particularly, to methods of improving propeller blade. Method includes increasing radius of initial circle (15, 25) of leading edge of each aerodynamic profile (10) of said blade, moving front edge (5) from semi-profiled strip (21) to side semi-profile (11) of back, thus changing aerodynamic profile (10) of each cross-section of said blade and curvature of each aerodynamic profile (10). As a consequence, negative critical angle of attack of said blade increases in absolute value.
EFFECT: higher aerodynamic characteristics of said blade at negative angle of attack compared to unmodified blade without significant deterioration of its aerodynamic characteristics at positive angle of attack.
12 cl, 12 dwg
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