Transonic airfoil, wing, and aircraft

Abstract

[Object] To provide a transonic airfoil capable of reducing pressure drag more than before, a wing having such an airfoil, and an aircraft including such a wing. [Solving Means] An airfoil 11 has a shape in which a pressure coefficient Cp of a static pressure in a chord direction of a leading edge 12 of the airfoil 11 is −0.04 or less at z/c=0.015 (where z represents a coordinate in a direction perpendicular to an airflow direction within a plane that forms an airfoil, with a leading edge being as a reference (an upper wing surface direction is positive, and a lower wing surface direction is negative), and c represents a chord length). Thus, a pressure distribution has a sharp rise, which can decrease pressure drag.

Dependencies are inferred from the claim text.