An airfoil for a rotary-wing aircraft blade of a rotary-wing aircraft, such as a helicopter, wherein 100% chord is defined as the position of the rear end with respect to the front end of the chord of the airfoil, upper-wing height is defined as being from the chord to the wing upper surface, and lower-wing height is defined as being from the chord to the wing lower surface. The airfoil for the rotary wing aircraft blade satisfies the following four conditions: Airfoil condition 1: wing thickness has a maximum within the range of 30-40% chord; Airfoil condition 2: the camber has a maximum within the range of 15-25% chord, and the camber slope changes from decreasing to increasing within the range of 45-55% chord; Airfoil condition 3: the upper-wing height has a maximum within the range of 25-35% chord; and Airfoil condition 4: the lower-wing height has a maximum within the range of 35-45% chord.
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