| 摘要 |
FIELD: aircraft engineering.SUBSTANCE: invention relates to aviation, particularly, to rotary-winged aircraft rotor and anti-torque propellers blades designs. Propeller blade consists of root part with mount fitting, middle part and end part, consisting of first section having sweepforward leading edge, and second section having backswept leading edge and sweepback trailing edge. Blade end part third section is its side edge connecting tip leading and trailing edges, has backward sweep from connection point with backward sweep second section to maximum blade span point and sweepforward from maximum blade span point to point of intersection with blade trailing edge. Beginning of tip leading edge first sweepforward section ris located in range of relative radii r/R=0.8÷0.865. Length of ledge drelative to blade main part leading edge continuation, referred to blade main part chord B is located in range d/B=0.23÷0.25.EFFECT: decreased blade hinge moments and reduced power losses for wave resistance overcoming.11 cl, 3 dwg |
