ANTITORQUE ROTOR BLADE AND ANTITORQUE ROTOR Russian patent published in 2013 - IPC B64C27/04 

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to helicopter antitorque rotors. Blade 6 of antitorque rotor 3 has opposed leading edge 8 and trailing edge 9 extending the blade lengthwise axis B. Trailing edge 9 interacts with airflow behind leading edge 8. Blade 6 has end part 14c extending between base section 51 and blade radially external end 11 with respect to rotational axis A. Said rotational axis A is located outside of blade 6 and across lengthwise axis B. Length d of chord Pat end part 14c decreases from base section 51 to outer end 11 while leading and trailing edges get connected at outer end 11. Chord length makes d₀ in base section to decrease therefrom to the end in compliance with the equation d=d₀(1-krⁿ), where r is the distance from base section while k and n are contact factors. Note here that coefficient n takes on the values from 2 to 11 while factor k equals 1/R where R is distance in radius from the end to base section.

EFFECT: higher aerodynamic efficiency, decreased noise.

10 cl, 18 dwg