| 摘要 |
PURPOSE: To improve aerodynamic performance and to reduce damage by providing a camber having a specific front edge and a rear edge and providing a plural number of airfoiled cross sections to taper from an airfoiled cross section adjacent to a root part to an airfoiled cross section adjacent to a head end part under a specific condition. CONSTITUTION: A main part of an airfoiled blade 10 on a propeller of an airplane is formed of a head end part 15 and a root part 20. In this case, a camber having a radiant front edge each cross section of which has an obtuse angle roughly along overall length, the maximum blade thickness of which is within a range of roughly 38%-42% of chord length and having a top point of roughly 45% of the chord length and a rear edge to be comparatively an obtuse angle are provided on the airfoiled blade 10. Thereafter, an airfoiled cross section having a thickness ratio of 20% adjacent to the root part 20 to an airfoiled cross section having a thickness ratio of 2% adjacent to the head end part 15 are tapered, and at the time of tapering these cross section parts, a plural number of airfoiled cross sections 23-206 to move a position of the airfoiled cross section maximum blade thickness roughly from 38% to 42% are provided.
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