A variable geometry turbocharger, comprising: a turbine rotor; and a variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from a scroll flow passage formed on a radially outer side of the turbine rotor, wherein the variable nozzle mechanism includes: at least one nozzle vane (14, 14A, 14B, 14C) disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane (14, 14A, 14B, 14C) rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction, and wherein, of an end surface of the nozzle vane (14, 14A, 14B, 14C) on a side of the non-support wall, an edge portion on a side of a pressure surface includes a non-support-wall side linear portion formed to have a linear shape, wherein an end portion of the nozzle vane (14, 14A, 14B, 14C) on a side of the non-support wall includes a non-support-wall side inclined surface connecting the end surface of the nozzle vane (14, 14A, 14B, 14C) on the side of the non-support wall and the pressure surface, wherein the non-support-wall side inclined surface is inclined so that a distance from a suction surface of the nozzle vane (14, 14A, 14B, 14C) to the non-support-wall side inclined surface reduces toward the non-support wall, and wherein the non-support-wall side linear portion is formed on a boundary position between the non-support-wall side inclined surface and the end surface on the side of the non-support wall. a turbine rotor; and a variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from a scroll flow passage formed on a radially outer side of the turbine rotor, wherein the variable nozzle mechanism includes: at least one nozzle vane (14, 14A, 14B, 14C) disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane (14, 14A, 14B, 14C) rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction, and at least one nozzle vane (14, 14A, 14B, 14C) disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane (14, 14A, 14B, 14C) rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction, and wherein, of an end surface of the nozzle vane (14, 14A, 14B, 14C) on a side of the non-support wall, an edge portion on a side of a pressure surface includes a non-support-wall side linear portion formed to have a linear shape, wherein an end portion of the nozzle vane (14, 14A, 14B, 14C) on a side of the non-support wall includes a non-support-wall side inclined surface connecting the end surface of the nozzle vane (14, 14A, 14B, 14C) on the side of the non-support wall and the pressure surface, wherein the non-support-wall side inclined surface is inclined so that a distance from a suction surface of the nozzle vane (14, 14A, 14B, 14C) to the non-support-wall side inclined surface reduces toward the non-support wall, and wherein the non-support-wall side linear portion is formed on a boundary position between the non-support-wall side inclined surface and the end surface on the side of the non-support wall.