STATIC BLADE AND AIRCRAFT GAS TURBINE ENGINE

A stator vane (30) provided rearward of a rotor blade (21), includes: an airfoil body (32) having an airfoil profile (31). The maximum airfoil thickness position (M) of the airfoil body (32) on the airfoil profile (31) satisfies following conditions at least on a tip side (30b) of the airfoil body (32): (a) on a plane expanded in a circumferential direction (CD) in which the stator vane (30) is arranged, the position (M) is located in a first region (33) which is close to a trailing edge (32b) of the airfoil body (32) from an intersection (IP) of the airfoil body (32) and a line (26) which is parallel to an extension line (28) of a camber line (27) of the rotor blade (21) at a trailing edge (21b) of the rotor blade (21) and passes through a leading edge (40a) of another stator vane (40) adjacent in the circumferential direction (CD), and (b) the position (M) is located in a second region (34) having a chord ratio from 0.2 to 0.8.