Wings of aircraft rotary wing with a sweep angle tip

摘要

PURPOSE: To prevent a shock wave, a stall, a blade/vortex mutual action by incorporating first to fourth areas along a longitudinal direction in the blade, changing wing chordal lengths according to a specific function in the areas, setting a change of a deviation of an aerodynamic center so that front and rear edges of the blade do not display any damage. ;CONSTITUTION: The blade has a first area between 75% and 87% of the entire length measured from a rotating axial center of a boss from an inner edge of the blade in a longitudinal direction, a second area between 87% and 93%, a third area between 93% and 97%, and a fourth area extended to a free outer edge of the blade. A wing chordal length L is substantially linearly long in the first area, changed according to a cubic function in the second area, and changes constant in the third area and according to a parabolic function in the fourth area. As a result, the blade exhibits a swept-back angle due to a deviation of an aerodynamic center to an axial center, and the front edge 5 and the rear edge 6 of the blade may not display any damage. The edge 5 of the blade is a protrusion or linear and the edge 6 becomes a recess or linear.;COPYRIGHT: (C)1994,JPO