A system includes a gas turbine combustor (16), which includes a combustion liner (42) disposed about a combustion region, a flow sleeve (44) disposed about the combustion liner (42), an air passage (46) between the combustion liner (42) and the flow sleeve (44), and an aerodynamic mounting assembly (66) disposed in the air passage (46). The aerodynamic mounting assembly (66) is configured to retain the combustion liner (42) within the flow sleeve (44). The aerodynamic mounting assembly (66) includes a flow sleeve mount (68) coupled to the flow sleeve (44) and a liner stop (70) coupled to the combustion liner (42). The flow sleeve mount (68) includes a first portion of an aerodynamic shape and the liner stop (70) includes a second portion of the aerodynamic shape, which is configured to direct an airflow (82) into a wake region (67) downstream of the aerodynamic mounting assembly (66). The flow sleeve mount (68) and the liner stop (70) couple with one another to define the aerodynamic shape.